Turbine blade and gas turbine
1. A turbine blade, comprising:
a blade body having leading and trailing edges opposite in a chordwise direction thereof, the blade body having a mid-chord located between the leading and trailing edges in the chordwise direction thereof, the mid-chord having a mid-chord cooling cavity located therein, the trailing edge having a trailing edge cooling cavity located therein, the trailing edge cooling cavity being located closer to the trailing edge than the mid-chord cooling cavity is located in the chordwise direction of the blade body; and
the trailing edge baffle plate extends along the height direction of the blade body, the trailing edge baffle plate is arranged in the trailing edge cooling cavity to divide the trailing edge cooling cavity into a plurality of cooling cavities including a first cooling cavity and a second cooling cavity, the second cooling cavity is arranged closer to the trailing edge than the first cooling cavity in the chord direction of the blade body, the blade body is provided with a blade top and a blade bottom which are opposite in the height direction, the blade bottom is provided with a middle chord cooling air inlet communicated with the middle chord cooling cavity, a trailing edge cooling air inlet communicated with the first cooling cavity and a second cooling air outlet communicated with the second cooling cavity, at least one part of the middle chord cooling cavity is communicated with the first cooling cavity, and the trailing edge baffle plate is provided with a jet hole extending along the chord direction of the blade body.
2. The turbine blade of claim 1, wherein said blade body defines a trailing edge cleft, said trailing edge cleft located between said second cooling cavity and said trailing edge in a chordwise direction of said blade body, said trailing edge cleft communicating with said second cooling cavity.
3. The turbine blade of claim 2, said second cooling cavity having fins disposed therein.
4. The turbine blade as in any one of claims 1-3, wherein the trailing edge baffle is provided in plurality, the plurality of trailing edge baffles being arranged at intervals in a chordwise direction of the blade body to divide the trailing edge cooling cavity into a plurality of cooling cavities including the first cooling cavity, the second cooling cavity, and a third cooling cavity, the third cooling cavity being located between the first cooling cavity and the second cooling cavity in the chordwise direction of the blade body, and a third cooling air outlet being provided on the blade root in communication with the third cooling cavity.
5. The turbine blade as in claim 4, wherein the plurality of jet holes on each of the trailing edge diaphragms are provided.
6. The turbine blade as in claim 5, wherein a plurality of said jet holes on adjacent two of said trailing edge partitions are in one-to-one correspondence.
7. The turbine blade as in claim 6, wherein corresponding two of the jet holes on adjacent two of the trailing edge bulkheads are staggered in a chordwise direction of the blade body.
8. The turbine blade as in claim 7, wherein each of the jet holes is arranged at an inclination such that a line connecting centers of corresponding two jet holes on adjacent two of the trailing edge partitions is parallel to a centerline of each of the two jet holes.
9. The turbine blade as in any one of claims 5-8, wherein the plurality of jet holes in each of the trailing edge partitions are arranged in a plurality of rows in a thickness direction of the blade body.
10. The turbine blade of any one of claims 1-3, wherein the mid-chord cooling cavity comprises a first mid-chord cooling cavity and a second mid-chord cooling cavity, the first mid-chord cooling cavity and the second mid-chord cooling cavity being spaced apart in a chordwise direction of the blade body;
the turbine blade further includes: the first middle chord partition plate extends along the height direction of the blade body, the first middle chord partition plate is arranged in the first middle chord cooling cavity, a U-shaped cooling channel is defined between the first middle chord partition plate and the cavity wall of the first middle chord cooling cavity, a first middle chord cooling air inlet communicated with the U-shaped cooling channel is formed in the blade bottom, and a first middle chord cooling air outlet communicated with the U-shaped cooling channel is formed in the blade body; and
the blade body is provided with a plurality of second mid-chord partition plates, each second mid-chord partition plate extends along the chord direction of the blade body, the second mid-chord partition plates are arranged in the second mid-chord cooling cavity at intervals along the height direction of the blade body, a serpentine cooling channel is defined between the second mid-chord partition plates and the cavity wall of the second mid-chord cooling cavity, a second mid-chord cooling air inlet communicated with the serpentine cooling channel is formed in the blade bottom, and a second mid-chord cooling air outlet communicated with the serpentine cooling channel is formed in the blade body.
11. The turbine blade of claim 10, wherein the second mid-chord cooling cavity is located between the first mid-chord cooling cavity and the trailing edge cooling cavity in a chordwise direction of the blade body, and the first mid-chord cooling air outlet is disposed on the blade root.
12. A gas turbine comprising a turbine blade, said turbine blade being a turbine blade as claimed in any one of claims 1 to 11.
Background
The gas turbine is an internal combustion type power machine which takes continuously flowing gas as cooling gas to drive a turbine to rotate at high speed and converts the energy of fuel into useful work, and is a rotary impeller type heat engine. Research shows that the power and the efficiency of the gas turbine can be improved by 10% every time the turbine inlet temperature of the gas turbine is improved by 55 ℃, so that the continuous improvement of the inlet air temperature becomes the necessary requirement of the development of the gas turbine. In the related art, the cooling effect of the turbine blade is not good, resulting in poor operational safety of the gas turbine.
Disclosure of Invention
The present invention is based on the discovery and recognition by the inventors of the following facts and problems:
the external flow from the edge of the turbine blade to the tail edge is complex, the heat load is high, the cooling structure of the turbine blade in the related art can only carry out local cooling on certain flow areas, and the cooling effect is poor. The invention sets corresponding cooling structures aiming at the structural characteristics of the middle chord and the tail edge, and improves the heat exchange capability of the turbine blade to the maximum extent within the allowable range of the manufacturing technology, and reduces the flow loss so as to improve the body cooling effect of the turbine blade, thereby improving the power and the efficiency of the gas turbine and maintaining the safe and stable operation of the gas turbine.
The present invention is directed to solving, at least to some extent, one of the technical problems in the related art.
Therefore, the embodiment of the invention provides a turbine blade with good cooling effect;
the embodiment of the invention provides a gas turbine, which aims to solve the technical problems of low power, low efficiency and poor operation safety of the gas turbine.
A turbine blade according to an embodiment of the present invention includes:
a blade body having leading and trailing edges opposite in a chordwise direction thereof, the blade body having a mid-chord located between the leading and trailing edges in the chordwise direction thereof, the mid-chord having a mid-chord cooling cavity located therein, the trailing edge having a trailing edge cooling cavity located therein, the trailing edge cooling cavity being located closer to the trailing edge than the mid-chord cooling cavity is located in the chordwise direction of the blade body; and
the trailing edge baffle plate extends along the height direction of the blade body, the trailing edge baffle plate is arranged in the trailing edge cooling cavity to divide the trailing edge cooling cavity into a plurality of cooling cavities including a first cooling cavity and a second cooling cavity, the second cooling cavity is arranged closer to the trailing edge than the first cooling cavity in the chord direction of the blade body, the blade body is provided with a blade top and a blade bottom which are opposite in the height direction, the blade bottom is provided with a middle chord cooling air inlet communicated with the middle chord cooling cavity, a trailing edge cooling air inlet communicated with the first cooling cavity and a second cooling air outlet communicated with the second cooling cavity, at least one part of the middle chord cooling cavity is communicated with the first cooling cavity, and the trailing edge baffle plate is provided with a jet hole extending along the chord direction of the blade body.
The turbine blade provided by the embodiment of the invention has the advantages of good cooling effect and the like.
In some embodiments, a trailing edge cleft is disposed on the blade body, the trailing edge cleft is located between the second cooling cavity and the trailing edge in the chord direction of the blade body, and the trailing edge cleft is communicated with the second cooling cavity.
In some embodiments, fins are disposed within the second cooling cavity.
In some embodiments, the trailing edge baffle is provided in plurality, the trailing edge baffles are arranged at intervals along the chordwise direction of the blade body to divide the trailing edge cooling cavity into a plurality of cooling cavities including the first cooling cavity, the second cooling cavity and a third cooling cavity, the third cooling cavity is located between the first cooling cavity and the second cooling cavity in the chordwise direction of the blade body, and a third cooling air outlet communicated with the third cooling cavity is provided on the blade bottom.
In some embodiments, the plurality of jet holes on each trailing edge baffle plate are provided.
In some embodiments, the plurality of jet holes on two adjacent trailing edge baffles are in one-to-one correspondence.
In some embodiments, two corresponding jet holes on two adjacent trailing edge partition plates are arranged in a staggered manner in the chordwise direction of the blade body.
In some embodiments, each of the jet holes is arranged obliquely so that a line connecting centers of two corresponding jet holes on two adjacent trailing edge partitions is parallel to a center line of each of the two jet holes.
In some embodiments, the plurality of jet holes in each trailing edge baffle are arranged in a plurality of rows in the thickness direction of the blade body.
In some embodiments, the mid-chord cooling cavity comprises a first mid-chord cooling cavity and a second mid-chord cooling cavity, the first mid-chord cooling cavity and the second mid-chord cooling cavity being spaced apart in a chordwise direction of the blade body;
the turbine blade further includes: the first middle chord partition plate extends along the height direction of the blade body, the first middle chord partition plate is arranged in the first middle chord cooling cavity, a U-shaped cooling channel is defined between the first middle chord partition plate and the cavity wall of the first middle chord cooling cavity, a first middle chord cooling air inlet communicated with the U-shaped cooling channel is formed in the blade bottom, and a first middle chord cooling air outlet communicated with the U-shaped cooling channel is formed in the blade body; and
the blade body is provided with a plurality of second mid-chord partition plates, each second mid-chord partition plate extends along the chord direction of the blade body, the second mid-chord partition plates are arranged in the second mid-chord cooling cavity at intervals along the height direction of the blade body, a serpentine cooling channel is defined between the second mid-chord partition plates and the cavity wall of the second mid-chord cooling cavity, a second mid-chord cooling air inlet communicated with the serpentine cooling channel is formed in the blade bottom, and a second mid-chord cooling air outlet communicated with the serpentine cooling channel is formed in the blade body.
In some embodiments, the second mid-chord cooling cavity is located between the first mid-chord cooling cavity and the trailing edge cooling cavity in a chordwise direction of the blade body, and the first mid-chord cooling gas outlet is disposed on the blade root.
A gas turbine according to an embodiment of the present invention includes a turbine blade that is a turbine blade according to an embodiment of the present invention.
The gas turbine provided by the embodiment of the invention has the advantages of high power, high efficiency, good operation safety and the like.
Drawings
FIG. 1 is a schematic structural view of a turbine blade according to one embodiment of the present invention.
Fig. 2 is a schematic view of the structure of fig. 1 from another perspective.
FIG. 3 is a schematic view of the internal structure of a turbine blade according to one embodiment of the invention.
Fig. 4 is a schematic view of the structure of fig. 3 from another view angle.
FIG. 5 is a schematic illustration of the distribution of cooling fluid for a turbine blade according to one embodiment of the present invention.
Fig. 6 is a schematic view of the structure of fig. 5 from another view angle.
Reference numerals: a turbine blade 100;
a blade body 1; a leading edge 101; a film hole 1011; a trailing edge 102; a middle chord 103; a leaf tip 104; a leaf bottom 105; a suction surface 106; a pressure surface 107; a middle chord 108;
a vortex chamber 2; an air inlet chamber 3; a leading edge cooling gas inlet 301; a leading edge partition 4; a leading edge channel 401;
a middle chord cooling cavity 5; a mid-chord cooling gas inlet 501; a mid-chord cooling gas outlet 502; a first mid-chord cooling cavity 6; a U-shaped cooling channel 601; a first mid-chord cooling gas inlet 602; a first mid-chord cooling gas outlet 603; a first mid-chord diaphragm 7; a second mid-chord cooling cavity 8; serpentine cooling channels 801; a second mid-chord cooling gas inlet 802; a second mid-chord cooling gas outlet 803; a second mid-chord diaphragm 9; a partition 10;
a trailing edge cooling cavity 11; a first cooling chamber 1101; trailing edge cooling gas inlet 11011; a second cooling chamber 1102; a second cooling gas outlet 11021; a third cooling chamber 1103; a third cooling gas outlet 11031; a trailing edge baffle 12; a jet hole 1200; a first trailing edge baffle 1201; a first jet hole 12011; a second trailing edge baffle 1202; a second jet hole 12021;
a trailing edge cleft 13;
the fins 14;
cooling the working medium 200;
an air intake portion 2001; a swirling portion 2002; a first communicating portion 20012; a gas film portion 2003;
a U-shaped cooling portion 2004;
serpentine cooling portion 2005; the second communicating portion 20051;
a first trailing edge cooling portion 2006; a second trailing edge cooling portion 2007; a third trailing edge cooling portion 2008; a first jet portion 2009; a second fluidic portion 2010; a split slit part 2011.
Detailed Description
Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention.
As shown in fig. 1 to 4, a turbine blade 100 according to an embodiment of the present invention includes a blade body 1 and a trailing edge diaphragm 12.
The blade body 1 has a leading edge 101 and a trailing edge 102 opposed in its chordwise direction, and the blade body 1 has a mid-chord 108 located between the leading edge 101 and the trailing edge 102 in its chordwise direction. A middle chord cooling cavity 5 is arranged at the middle chord 108, a tail edge cooling cavity 11 is arranged at the tail edge 102, and the tail edge cooling cavity 11 is arranged closer to the tail edge 102 than the middle chord cooling cavity 5 in the chord direction of the blade body 1.
A trailing edge baffle 12 extends in the height direction of the blade body 1, and the trailing edge baffle 12 is provided within the trailing edge cooling chamber 11 to divide the trailing edge cooling chamber 11 into a plurality of cooling chambers including a first cooling chamber 1101 and a second cooling chamber 1102 provided closer to the trailing edge than the first cooling chamber in the chord direction of the blade body. The blade body 1 has a blade tip 104 and a blade root 105 which are opposite in the height direction thereof, and the blade root 105 is provided with a middle chord cooling air inlet 501 which is communicated with the middle chord cooling cavity 5, a tail edge cooling air inlet 11011 which is communicated with the first cooling cavity 1101, and a second cooling air outlet 11021 which is communicated with the second cooling cavity 1102. At least a part of the mid-chord cooling chamber 5 communicates with the first cooling chamber 1101, and the trailing edge partition 12 is provided with a jet hole 1200 extending in the chordwise direction of the blade body 1.
Therefore, a trailing edge cooling working medium (trailing edge cooling air) enters the first cooling cavity 1101 through a trailing edge cooling air inlet 11011, part or all of the middle chord cooling working medium flowing out of the middle chord cooling cavity 5 also enters the first cooling cavity 1101, the cooling working medium (the trailing edge cooling working medium and the middle chord cooling working medium flowing into the first cooling cavity 1101) entering the first cooling cavity 1101 exchanges heat with the trailing edge 102, and then part or all of the cooling working medium entering the first cooling cavity 1101 flows out through a second cooling air outlet 11021 to be recovered.
As at least one part of the middle chord cooling cavity 5 is communicated with the first cooling cavity 1101, at least one part of the middle chord cooling cavity 5 is communicated with the tail edge cooling cavity 11, so that at least one part of the middle chord cooling cavity 5 is coupled with the tail edge cooling cavity 11, the speed of the cooling working medium entering the second cooling cavity 1102 from the jet hole 1200 is higher, the impact cooling is carried out on the tail edge 102 where the second cooling cavity 1102 is arranged, the cooling effect at the tail edge 102 is improved, the power and the efficiency of the gas turbine are improved, and the safe and stable operation of the gas turbine is maintained.
Therefore, the turbine blade 100 according to the embodiment of the present invention has advantages such as a good cooling effect.
The turbine blade 100 according to an embodiment of the present invention is described in detail below with reference to the accompanying drawings.
As shown in fig. 1 to 4, a turbine blade 100 according to an embodiment of the present invention includes a blade body 1, the blade body 1 having a leading edge 101 and a trailing edge 102 opposed in a chordwise direction thereof. The blade body 1 has a mid-chord 108 located between the leading edge 101 and the trailing edge 102 in the chordwise direction thereof. The blade body 1 has a tip 104 and a bottom 105 opposed to each other in the height direction thereof.
In some embodiments, a leading edge cooling cavity is provided at the leading edge 101.
The turbine blade 100 further includes a leading edge partition 4, the leading edge partition 4 extending in the height direction of the blade body 1, the leading edge partition 4 being provided in the leading edge cooling chamber to divide the leading edge cooling chamber into the swirling flow chamber 2 and the intake chamber 3. The swirl chamber 2 is disposed closer to the leading edge 101 than the intake chamber 3 in the chord direction of the blade body 1. The blade bottom 105 is provided with a leading edge cooling air inlet 301 communicated with the air inlet cavity 3 and a leading edge cooling air outlet 201 communicated with the swirling flow cavity 2. The leading edge partition 4 is provided with a leading edge passage 401 communicating with each of the swirling flow chamber 2 and the intake chamber 3.
Therefore, the front edge cooling working medium (front edge cooling air) enters the air inlet cavity 3 through the front edge cooling air inlet 301, then enters the cyclone cavity 2 through the front edge channel 401 on the front edge partition plate 4, flows along the circular arc structure at the position of the front edge 101 in the cyclone cavity 2, and then partially or completely flows out of the front edge cooling air outlet 201 to be recovered. Due to the arc-shaped structure at the position of the front edge 101, the front edge cooling working medium can generate vortices in the vortex chamber 2, so that the development of a front edge cooling working medium boundary layer is effectively damaged, the heat exchange effect at the position of the front edge 101 is enhanced, the cooling effect at the position of the front edge 101 is improved, the power and the efficiency of the gas turbine are improved, and the safe and stable operation of the gas turbine is maintained.
For example, as shown in fig. 3 and 4, the chord direction of the blade body 1 is the front-rear direction, the leading edge 101 is provided on the front side of the trailing edge 102, and the swirl chamber 2 is provided on the front side of the intake chamber 3.
Preferably, the leading edge channel 401 is provided in plurality, and the plurality of leading edge channels 401 are arranged at intervals in the height direction of the blade body 1.
Therefore, the front edge working medium in the air inlet cavity 3 respectively enters the cyclone cavity 2 through the front edge channels 401, and flows along the arc-shaped structure at the front edge 101 position in the cyclone cavity 2 to generate a vortex, so that the front edge 101 is cooled. Because the front edge channels 401 are arranged at intervals along the height direction of the blade body 1, front edge working media are arranged at each position in the swirling flow cavity 2 and the air inlet cavity 3, cooling of each part at the front edge 101 is achieved, the cooling effect at the front edge 101 is improved, the power and the efficiency of the gas turbine are further improved, and safe and stable operation of the gas turbine is maintained.
In some embodiments, the blade body 1 has the suction side 106 and the pressure side 107 opposite in its thickness direction, and the leading edge channel 401 is arranged adjacent to the suction side 106 or the pressure side 107 in the thickness direction of the blade body 1.
Therefore, the front edge working medium in the air inlet cavity 3 flows into the vortex cavity 2 in a mode of being adjacent to or even attached to the suction surface 106 or the pressure surface 107, so that the front edge working medium entering the vortex cavity 2 can easily flow along the arc-shaped structure at the position of the edge 101 and generate vortices, the development of a front edge cooling working medium boundary layer is effectively damaged, and the heat exchange effect at the position of the front edge 101 is enhanced.
For example, as shown in FIGS. 3 and 4, the leading edge channel 401 is disposed on the side of the leading edge partition 4 adjacent to the pressure surface 107. The leading working medium in the inlet chamber 3 thus flows into the swirl chamber 2 against the pressure surface 107 and along the walls of the swirl chamber 2.
In some embodiments, the leading edge 101 is provided with a film hole 1011 communicating with the swirl chamber 2.
Therefore, on one hand, a part of front edge working medium passing through the cyclone cavity 2 flows out through the air film hole 1011, so that fluid mixing at the front edge 101 of the blade is enhanced, and the front edge 101 is effectively cooled; on the other hand, the front edge working medium flowing out of the air film hole 1011 can form an air film near the air film hole 1011, so that the front edge 101 is effectively prevented from being directly contacted with a high-temperature main stream, and the temperature of the front edge 101 is prevented from being too high. The power and the efficiency of the gas turbine are further improved, and the safe and stable operation of the gas turbine is maintained.
In some embodiments, the plurality of film holes 1011 are provided, and the plurality of film holes 1011 are arranged at intervals in the height direction of the blade body 1.
Therefore, the plurality of air film holes 1011 arranged at intervals along the height direction of the blade body 1 are beneficial to further enhancing the fluid mixing at the front edge 101 of the blade and effectively cooling the front edge 101; and a plurality of air films can be formed on the front edge 101 along the height direction of the blade body 1, so that the front edge 101 is effectively prevented from being in direct contact with a high-temperature main flow, the power and the efficiency of the gas turbine are further improved, and the safe and stable operation of the gas turbine is maintained.
In some embodiments, the blade body 1 has a mid-chord 108 located between the leading edge 101 and the trailing edge 102 in the chordwise direction thereof, the mid-chord cooling cavity 5 is provided at the mid-chord 108, the blade bottom 105 is provided with a mid-chord cooling gas inlet 501 communicating with the mid-chord cooling cavity 5, and the blade body 1 is provided with a mid-chord cooling gas outlet 502 communicating with the mid-chord cooling cavity 5.
For example, as shown in fig. 3 and 4, taking the chordwise direction of the blade body 1 as the front-rear direction, the leading edge 101 is disposed on the front side of the trailing edge 102, and the leading edge cooling cavity is disposed on the front side of the mid-chord cooling cavity 5.
Therefore, a middle chord cooling working medium (middle chord cooling gas) enters the middle chord cooling cavity 5 through the middle chord cooling gas inlet 501, exchanges heat with the middle chord 108 between the front edge 101 and the tail edge 102, and then flows out through the middle chord cooling gas outlet 502 to be recovered, so that the middle chord 108 is cooled, the power and the efficiency of the gas turbine are further improved, and the safe and stable operation of the gas turbine is maintained.
In some embodiments, the mid-chord cooling cavity 5 includes a first mid-chord cooling cavity 6 and a second mid-chord cooling cavity 8, the first mid-chord cooling cavity 6 and the second mid-chord cooling cavity 8 being spaced apart in a chordwise direction of the blade body 1.
The turbine blade 100 also includes a first mid-chord diaphragm 7 and a plurality of second mid-chord diaphragms 9.
The first middle chord clapboard 7 extends along the height direction of the blade body 1, the first middle chord clapboard 7 is arranged in the first middle chord cooling cavity 6, and a U-shaped cooling channel 601 is defined between the first middle chord clapboard 7 and the cavity wall of the first middle chord cooling cavity 6. The blade bottom 105 is provided with a first middle chord cooling air inlet 602 communicated with the U-shaped cooling channel 601, and the blade body 1 is provided with a first middle chord cooling air outlet 603 communicated with the U-shaped cooling channel 601.
Each second mid-chord partition 9 extends along the chordwise direction of the blade body 1, a plurality of second mid-chord partitions 9 are arranged in the second mid-chord cooling cavity 8 at intervals along the height direction of the blade body 1, and a serpentine cooling channel 801 is defined between the plurality of second mid-chord partitions 9 and the cavity wall of the second mid-chord cooling cavity 8. The blade bottom 105 is provided with a second middle chord cooling air inlet 802 communicated 801 with the serpentine cooling channel, and the blade body 1 is provided with a second middle chord cooling air outlet 803 communicated 801 with the serpentine cooling channel.
The first mid-chord cooling gas inlet 602 and the second mid-chord cooling gas inlet 802 are both mid-chord cooling gas inlets 501, and the first mid-chord cooling gas outlet 603 and the second mid-chord cooling gas outlet 803 are both mid-chord cooling gas outlets 502.
For example, as shown in fig. 3 and 4, taking the chordwise direction of the blade body 1 as the front-rear direction, the leading edge 101 is disposed on the front side of the trailing edge 102, and the first midchord cooling cavity 6 is disposed on the front side of the second midchord cooling cavity 8.
Therefore, a part of the middle chord cooling working medium enters the U-shaped cooling channel 601 through the first middle chord cooling air inlet 602, exchanges heat with the middle chord part provided with the first middle chord cooling cavity 6, and then flows out through the first middle chord cooling air outlet 603 to be recovered. The other part of the middle chord cooling working medium enters the serpentine cooling channel 801 through the second middle chord cooling gas inlet 802, the part of the middle chord cooling working medium exchanges heat with the middle chord part provided with the second middle chord cooling cavity 8, and then the part of the middle chord cooling working medium flows out through the second middle chord cooling gas outlet 803 to be recovered, so that cooling at the middle chord 108 is realized.
Because the U-shaped cooling channel 601 has only two flows at the same time, the resistance loss of the middle chord cooling working medium in the first middle chord cooling cavity 6 is easy to control in a reasonable range. Because the middle chord cooling working medium in the serpentine cooling channel 801 actually flows along the axial direction of the turbine, the middle chord cooling working medium in the second middle chord cooling cavity 8 can overcome the adverse effect of the rotary Coriolis force, the uniformity of a flow field is ensured, and the heat exchange performance at the middle chord 108 is enhanced.
Therefore, the sizes and positions of the U-shaped cooling channel 601 and the snakelike cooling channel 801 in the chord direction can be reasonably set according to the specific structure of the middle chord 108 of the blade body 1, the properties of the middle chord cooling working medium, the working condition of high-temperature main flow and the like, so that the uniformity of a flow field at the middle chord 108 is ensured and the heat exchange performance at the middle chord 108 is enhanced under the condition that the resistance of the middle chord cooling working medium is controlled within a reasonable range.
In some embodiments, the first mid-chord cooling cavity 6 is located between the leading edge cooling cavity and the second mid-chord cooling cavity 8 in a chordwise direction of the blade body 1, and the first mid-chord cooling gas outlet 603 is disposed on the blade root 105. In other words, the second midswird cooling cavity 8 is located between the first midswird cooling cavity 6 and the trailing edge cooling cavity 11 in the chordwise direction of the blade body 1, and the first midswird cooling gas outlet 603 is provided on the blade bottom 105.
Thus, the cooling medium flowing out of the first middle chord cooling gas outlet 603 is convenient to recover.
At the trailing edge 102 a trailing edge cooling cavity 11 is provided.
The turbine blade 100 further includes a trailing edge diaphragm 12, the trailing edge diaphragm 12 extending in the height direction of the blade body 1, the trailing edge diaphragm 12 being provided within the trailing edge cooling cavity 11 to divide the trailing edge cooling cavity 11 into a plurality of cooling cavities including a first cooling cavity 1101 and a second cooling cavity 1102. The second cooling cavity 1102 is disposed closer to the trailing edge 102 than the first cooling cavity 1101 in the chordwise direction of the blade body 1. The blade base 105 is provided with a trailing edge cooling gas inlet 11011 communicated with the first cooling cavity 1101 and a second cooling gas outlet 11021 communicated with the second cooling cavity 1102. The middle chord cooling cavity 5 is located between the leading edge cooling cavity and the trailing edge cooling cavity 11 in the chordwise direction of the blade body 1, at least a part of the middle chord cooling cavity 5 is communicated with the first cooling cavity 1101, and the trailing edge partition plate 12 is provided with jet holes 1200 extending in the chordwise direction of the blade body 1.
For example, a partition 10 is provided between the mid-chord cooling cavity 5 and the first cooling cavity 1101, and a second mid-chord cooling gas outlet 803 is provided on the partition 10, thereby enabling communication of at least a portion of the mid-chord cooling cavity 5 with the first cooling cavity 1101.
For example, as shown in fig. 3 and 4, taking the chordwise direction of the blade body 1 as the front-rear direction, the leading edge 101 is disposed on the front side of the trailing edge 102, the midchord cooling cavity 5 is disposed on the front side of the trailing edge cooling cavity 11, and the first cooling cavity 1101 is disposed on the front side of the second cooling cavity 1102.
In some embodiments, the blade body 1 is provided with a tail edge split slit 13, the tail edge split slit 13 is located between the second cooling cavity 1102 and the tail edge 102 in the chord direction of the blade body 1, and the tail edge split slit 13 is communicated with the second cooling cavity 1102.
Therefore, one part of the cooling working medium entering the first cooling cavity 1101 flows out through the second cooling gas outlet 11021, the other part of the cooling working medium entering the first cooling cavity 1101 flows out through the tail edge cleft 13, the cooling working medium flowing out through the tail edge cleft 13 can cover the outer surface of the tail edge 102 to form an air film, direct contact between the tail edge 102 and a high-temperature main flow is effectively avoided, and the temperature of the tail edge 102 is prevented from being too high. The power and the efficiency of the gas turbine are further improved, and the safe and stable operation of the gas turbine is maintained.
In some embodiments, fins 14 are provided within the second cooling chamber 1102.
Because the speed of the cooling working medium entering the second cooling chamber 1102 from the jet hole 1200 is high, the cooling working medium entering the second cooling chamber 1102 passes through the fins 14 in a convection mode, the development of a flowing boundary layer is damaged, the fluid mixing is enhanced, meanwhile, closed vortexes near the trailing edge 102 of the fins 14 are reduced, the pressure loss of the cooling working medium is further reduced, the cooling working medium can flow out through the trailing edge cleft 13, and the cooling of the trailing edge 102 is realized.
In some embodiments, the trailing edge baffle 12 is provided in plurality, and the plurality of trailing edge baffles 12 are arranged at intervals in the chordwise direction of the blade body 1 to divide the trailing edge cooling cavity 11 into a plurality of cooling cavities including the first cooling cavity 1101, the second cooling cavity 1102, and the third cooling cavity 1103. The third cooling chamber 1103 is located between the first cooling chamber 1101 and the second cooling chamber 1102 in the chord direction of the blade body 1, and a third cooling gas outlet 11031 communicating with the third cooling chamber 1103 is provided in the blade base 105.
For example, as shown in fig. 3 and 4, the chordwise direction of the blade body 1 is taken as the front-rear direction, the leading edge 101 is provided on the front side of the trailing edge 102, and two trailing edge bulkheads 12 are provided. The two trailing edge partition plates 12 are respectively a first trailing edge partition plate 1201 and a second trailing edge partition plate 1202, the jet hole 1200 provided on the first trailing edge partition plate 1201 is a first jet hole 12011, and the jet hole provided on the second trailing edge partition plate 1202 is a second jet hole. First trailing edge baffle 1201 is disposed on the forward side of second trailing edge baffle 1202 such that first cooling cavity 1101 is disposed on the forward side of second cooling cavity 1102 and second cooling cavity 1102 is disposed on the forward side of third cooling cavity 1103.
Therefore, the trailing edge cooling working medium enters the first cooling cavity 1101 through the trailing edge cooling air inlet 11011, part or all of the middle chord cooling working medium flowing out of the middle chord cooling cavity 5 also enters the first cooling cavity 1101, and the cooling working medium entering the first cooling cavity 1101 enters the third cooling cavity 1103 through the first jet holes 12011 to exchange heat with the trailing edge 102 provided with the third cooling cavity 1103. Then, a part of the cooling working medium entering the third cooling cavity 1103 flows out through a third cooling gas outlet 11031 to be recycled; another portion of the cooling medium entering the third cooling chamber 1103 enters the second cooling chamber 1102 through the second jet holes 12021. And finally, part or all of the cooling working medium entering the second cooling cavity 1102 flows out through a second cooling gas outlet 11021 to be recovered.
Because at least a part of the middle chord cooling cavity 5 is coupled with the trailing edge cooling cavity 11, the cooling medium entering the third cooling cavity 1103 from the first jet hole 12011 and the cooling medium entering the second cooling cavity 1102 from the second jet hole 12021 both flow out quickly, so that the trailing edge 102 provided with the second cooling cavity 1102 and the third cooling cavity 1103 is subjected to impingement cooling, the cooling effect at the trailing edge 102 is further improved, the power and efficiency of the gas turbine are improved, and the safe and stable operation of the gas turbine is maintained.
It should be noted that the turbine blade 100 shown in fig. 3 and 4 is provided with only one third cooling cavity 1103, and in other embodiments, a plurality of third cooling cavities may be provided on the turbine blade, and the plurality of third cooling cavities are arranged at intervals along the chord direction.
In some embodiments, there are multiple jet holes 1200 on each trailing edge baffle 12.
Therefore, the flow velocity of the cooling working medium passing through the jet hole 1200 is favorably improved, the impact cooling effect of the cooling working medium on the trailing edge 102 is favorably improved, and the cooling effect on the trailing edge 102 is favorably further improved.
In some embodiments, there is a one-to-one correspondence between the plurality of jet holes 1200 on two adjacent trailing edge partitions 12.
Therefore, the pressure loss of the cooling working medium passing through the jet hole 1200 is favorably reduced, the impact cooling effect of the cooling working medium on the trailing edge 102 is favorably improved, and the cooling effect on the trailing edge 102 is favorably further improved.
In some embodiments, the two corresponding jet holes 1200 on two adjacent trailing edge partitions 12 are arranged in a staggered manner in the chordwise direction of the blade body 1.
This further contributes to an improvement in the impingement cooling effect of the cooling medium on the trailing edge 102, and further contributes to an improvement in the cooling effect on the trailing edge 102.
In some embodiments, each jet hole 1200 is disposed obliquely so that a line connecting the centers of the corresponding two jet holes 1200 on the adjacent two trailing edge partitions 12 is parallel to the center line of each of the two jet holes 1200.
Therefore, the cooling working medium flowing out of the jet hole 1200 of the upstream trailing edge partition plate 12 directly enters the jet hole 1200 of the downstream trailing edge partition plate 12 without changing the flow direction, which is beneficial to reducing the pressure loss of the cooling working medium passing through the jet hole, further beneficial to improving the impact cooling effect of the cooling working medium on the trailing edge 102, and beneficial to further improving the cooling effect on the trailing edge 102.
In some embodiments, the plurality of jet holes 1200 of each of the plurality of trailing edge partitions 12 are provided in a plurality of rows in the thickness direction of the blade body 1.
Therefore, the plurality of jet holes 1200 are arranged in order on the trailing edge baffle 12, which facilitates the design and processing of the trailing edge baffle 12.
As shown in FIGS. 5 and 6, when the turbine blade 100 is operating stably, the cooling medium 200 in the turbine blade 100 at a certain time is divided into three parts, namely a leading edge cooling medium part, a middle chord cooling medium part and a trailing edge cooling medium part, wherein the leading edge cooling medium part is used for cooling the leading edge 101, the middle chord cooling medium part is used for cooling the middle chord 108, and the trailing edge cooling medium part is used for cooling the trailing edge 102.
Specifically, the leading edge cooling charge portion includes an air intake portion 2001, a swirl portion 2002, a first communication portion 20012, and an air film portion 2003. The air inlet portion 2001 is located in the air inlet chamber 3, the swirling portion 2002 is located in the swirling chamber 2, the first communicating portion 20012 is located in the leading edge passage 401, and the film portion 2003 is located at the film hole 1011.
The mid-chord cooling working medium portion comprises a U-shaped cooling portion 2004, a serpentine cooling portion 2005 and a second communication portion 20051. A U-shaped cooling portion 2004 is located within the U-shaped cooling channel 601, a serpentine cooling portion 2005 is located within the serpentine cooling channel 801, and a second communication portion 20051 is located within the second midchord cooling gas outlet 803.
The trailing edge cooling working substance portions include a first trailing edge cooling portion 2006, a second trailing edge cooling portion 2007, a third trailing edge cooling portion 2008, a first jet portion 2009, a second jet portion 2010, and a split portion 2011. The first trailing edge cooling portion 2006 is located within the first cooling chamber 1101, the second trailing edge cooling portion 2007 is located within the second cooling chamber 1102, the third trailing edge cooling portion 2008 is located within the third cooling chamber 1103, the first jet portion 2009 is located within the first jet orifice 12011, the second jet portion 2010 is located within the second jet orifice 12021, and the split portion 2011 is located at the trailing edge split 13.
According to the turbine blade 100 provided by the embodiment of the invention, the air inlet cavity 3, the rotational flow cavity 2 and the air film hole 1011 are arranged at the front edge 101 to realize rotational flow cooling at the front edge 101, so that the arc-shaped molded line at the front edge 101 of the blade body 1 is fully utilized, the development of a boundary layer can be effectively destroyed after a cooling working medium enters, and the enhanced heat transfer effect is improved; the U-shaped cooling channel 601 and the serpentine cooling channel 801 are arranged at the middle chord 108, the U-shaped cooling channel 601 can control resistance loss within a reasonable range while strengthening heat transfer at the middle chord 108, and the serpentine cooling channel 801 can overcome the adverse effect of rotary coriolis force and enhance heat transfer performance; the trailing edge partition plate 12 and the jet holes 1200 are arranged at the trailing edge 102, impact cooling is carried out on the trailing edge 102 of the suction surface 106 and the pressure surface 107, development of a broken flow boundary layer can be helped, fluid mixing is enhanced, meanwhile, a cooling working medium covers the outer surface of the trailing edge 102 to form an air film, and direct contact between the trailing edge 102 and a high-temperature main flow is effectively avoided.
The arrangement of the cooling structure can obtain good heat transfer enhancement and drag reduction effects while ensuring the structural strength of the blade body 1. Compared with the traditional cooling structure, the turbine blade 100 provides an integral cooling scheme for the high-temperature turbine blade, and has the advantages of simple structure, convenience in processing, high heat transfer, low flow resistance and the like.
In addition, the cooling gas inlet and the cooling gas outlet are both provided on the blade bottom 105, and an independent cooling medium supply and recovery system may be provided.
The supply quantities of the front edge cooling working medium, the middle chord cooling working medium and the tail edge cooling working medium can be conveniently regulated and controlled through the flow of the corresponding cooling gas inlet and the cooling gas outlet, so that comprehensive and comprehensive cooling effect is achieved.
The gas turbine according to the embodiment of the present invention includes a turbine blade 100, and the turbine blade 100 is the turbine blade 100 according to the embodiment of the present invention.
Since the turbine blade 100 according to the embodiment of the present invention has advantages such as a good cooling effect. Therefore, the gas turbine provided by the embodiment of the invention has the advantages of high power, high efficiency, good operation safety and the like.
In the description of the present invention, it is to be understood that the terms "central," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," "axial," "radial," "circumferential," and the like are used in the orientations and positional relationships indicated in the drawings for convenience in describing the invention and to simplify the description, and are not intended to indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and are therefore not to be considered limiting of the invention.
Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In the description of the present invention, "a plurality" means at least two, e.g., two, three, etc., unless specifically limited otherwise.
In the present invention, unless otherwise expressly stated or limited, the terms "mounted," "connected," "secured," and the like are to be construed broadly and can, for example, be fixedly connected, detachably connected, or integrally formed; may be mechanically coupled, may be electrically coupled or may be in communication with each other; they may be directly connected or indirectly connected through a middle chord medium, or they may be connected internally or in any other manner known to those skilled in the art, unless otherwise specifically limited. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
In the present invention, unless expressly stated or limited otherwise, the first feature "on" or "under" the second feature may be directly contacting the first or second feature or indirectly contacting the first or second feature through a middle chord medium. Also, a first feature "on," "over," and "above" a second feature may be directly or diagonally above the second feature, or may simply indicate that the first feature is at a higher level than the second feature. A first feature being "under," "below," and "beneath" a second feature may be directly under or obliquely under the first feature, or may simply mean that the first feature is at a lesser elevation than the second feature.
In the present disclosure, the terms "one embodiment," "some embodiments," "an example," "a specific example," or "some examples" and the like mean that a specific feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the present disclosure. In this specification, the schematic representations of the terms used above are not necessarily intended to refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Furthermore, various embodiments or examples and features of different embodiments or examples described in this specification can be combined and combined by one skilled in the art without contradiction.
Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made to the above embodiments by those of ordinary skill in the art within the scope of the present invention.
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