JP2011163123A - Turbine moving blade - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To sufficiently suppress high temperature of a first squealer 11 and a second squealer 13 by utilizing not only film cooling but also convection cooling with respect to the first squealer 11 and second squealer 13. <P>SOLUTION: A first fillet portion 23 having a triangular cross section is integrally formed from the tip end surface 3t of a moving blade body 3 to the side of the tip end of the first squealer 11. A second fillet portion 25 having the triangular cross section is integrally formed from the tip end surface 3t of the moving blade body 3 to the side of the tip end of the second squealer 13. A plurality of tip blowout holes 27 are formed in the tip end surface 3t of the moving blade body 3 to communicate with a cooling passage 17. A plurality of communication blowout holes 29 are formed from the inner-side corner 3cv of the moving blade body 3 on the side of an inner tip end to the outer surface 11s of the first squealer 11. A plurality of radiation pin fins 31 are formed in the inner-side corner 3cv of the moving blade body 3 on the side of the inner tip end. <P>COPYRIGHT: (C)2011,JPO&INPIT

Description

  The present invention relates to a turbine rotor blade used in a turbine of a gas turbine engine such as an aircraft engine or an industrial gas turbine engine.

  Turbine rotor blades are exposed to combustion gas during operation of the gas turbine engine, and normally the compressed air extracted from the compressor or fan of the gas turbine engine is used as cooling air to increase the temperature of the turbine rotor blade. (Refer to Patent Document 1 and Patent Document 2). Specifically, a cooling passage through which cooling air (a part of the compressed air) can flow is formed inside the rotor blade body in the turbine rotor blade. Further, a plurality of blowout holes through which cooling air can be blown out are formed in the blade surface (front edge, abdominal surface) of the rotor blade body so as to communicate with the cooling passage.

  Therefore, during operation of the gas turbine engine, the cooling air extracted from the compressor or the fan flows into the cooling passage, so that the rotor blade body can be convectively cooled (internal cooling) from the inside. In addition, the cooling air that contributed to the convection cooling of the blade main body is blown out from the plurality of blow holes to form film cooling air that covers the blade main body, and film cooling (external cooling) of the blade main body Can do.

  On the other hand, in order to increase the turbine efficiency of a gas turbine engine, a turbine blade including a squealer that can be cooled using cooling air has been developed (see Non-Patent Document 1). Specifically, as shown in FIGS. 10 and 11, a squealer 107 that allows contact with the stationary component 105 of the turbine is integrally formed on the tip surface 103 t of the rotor blade body 103 of the turbine rotor blade 101. . Further, a plurality of tip blowing holes 109 through which the cooling air CA can be blown out are formed in communication with the cooling passage 111 at the distal end side and the distal end surface 103t of the abdominal surface 103v of the rotor blade body 103. 10 is an enlarged cross-sectional view taken along line XX in FIG. 11, and FIG. 11 is a partial perspective view of the turbine rotor blade according to the prior art.

  Therefore, the squealer 107 can be brought close to the stationary part 105 of the turbine, and the gap between the squealer 107 and the stationary part 105 of the turbine can be set as small as possible, from the side of the abdominal surface 103v of the moving blade body 103 during operation of the gas turbine engine. The clearance flow of the combustion gas G on the back surface 103b side can be reduced, and the turbine efficiency of the gas turbine engine can be increased. Further, during the operation of the gas turbine engine, as described above, in addition to the convection cooling and film cooling of the moving blade body 103, the cooling air CA contributing to the convection cooling of the moving blade body 103 is emitted from the plurality of tip blowout holes 109. By blowing out, film cooling air covering the squealer 107 can be formed, and the squealer 107 can be cooled.

  In addition, there exist some which are shown to patent document 3 and patent document 4 as a prior art relevant to this invention.

JP 7-293202 A JP-A-9-280002 JP 2003-56302 A JP 2006-105084 A

ASME GT2007-27066

  By the way, although the moving blade body 103 can be efficiently cooled by utilizing convection cooling and film cooling, only film cooling is utilized for the squealer 107, and convection cooling is hardly utilized. Therefore, there is a problem that the temperature of the squealer 107 cannot be sufficiently suppressed, and the life of the turbine rotor blade 101 is shortened.

  Therefore, an object of the present invention is to provide a turbine blade having a novel configuration that can solve the above-described problems.

  A feature of the present invention is a turbine blade that is used in a turbine of a gas turbine engine and can be cooled using cooling air, and a rotor blade body that obtains rotational force by combustion gas (mainstream gas); A squealer that is integrally formed on a tip surface and allows contact with a stationary component of the turbine, and a cooling passage through which cooling air can flow is formed inside the blade body, and the blade surface of the blade body A plurality of blowout holes through which cooling air can be blown out are formed in communication with the cooling passage, and a fillet portion having a triangular cross section is formed from the tip surface of the rotor blade body to the tip side of the inner surface of the squealer. The gist of the invention is that a tip blowing hole for blowing cooling air is formed in communication with the cooling passage on the tip surface of the blade body.

  Note that the wing surface includes a front edge, a rear edge, an abdominal surface, and a back surface.

  According to the characteristics of the present invention, the moving blade body can be convectively cooled (internally cooled) from the inside by cooling air flowing into the cooling passage during operation of the gas turbine engine. Further, the cooling air that contributes to the convection cooling of the blade main body is blown out from the plurality of blowout holes and the plurality of tip blowout holes, thereby forming film cooling air that covers the blade main body and the squealer. The blade main body and the squealer can be film-cooled (externally cooled).

  Here, since the fillet portion having a triangular cross section is formed from the tip surface of the rotor blade body to the tip side of the inner surface of the squealer, the space between the tip side of the squealer and the inner tip surface of the rotor blade body. The heat transfer area (in other words, the heat transfer area between the tip side of the squealer and the cooling passage) is increased to sufficiently transfer the heat from the squealer to the inner tip surface side of the rotor blade body. Can be secured. Thereby, during operation of the gas turbine engine, the squealer can be efficiently cooled by utilizing not only film cooling but also convection cooling for the squealer.

  According to the present invention, during the operation of the gas turbine engine, the squealer can be efficiently cooled by utilizing not only film cooling but also convection cooling for the squealer. Therefore, the life of the turbine rotor blade can be extended.

It is an expanded sectional view along II in FIG. It is a perspective view of the turbine rotor blade concerning a 1st embodiment. It is sectional drawing of the turbine rotor blade which concerns on 1st Embodiment. It is sectional drawing which shows the principal part of the turbine rotor blade concerning 2nd Embodiment, Comprising: It is a figure corresponded in FIG. It is sectional drawing which shows the principal part of the turbine bucket which concerns on 3rd Embodiment, Comprising: It is a figure equivalent to FIG. It is sectional drawing which shows the principal part of the turbine rotor blade concerning 4th Embodiment, Comprising: It is a figure corresponded in FIG. FIG. 7A is a cross-sectional view showing the main part of the turbine rotor blade according to the fifth embodiment, which corresponds to FIG. 1 and FIG. 7B is a view taken along the arrow VII in FIG. FIG. FIG. 8A is a cross-sectional view showing the main part of the turbine rotor blade according to the sixth embodiment, which corresponds to FIG. 1, and FIGS. 8B and 8C are the views in FIG. It is a figure which shows arrow VIII. FIG. 9A is a cross-sectional view showing the main part of the turbine rotor blade according to the seventh embodiment, which corresponds to FIG. 1, and FIG. 7B is an arrow XI in FIG. 9A. FIG. It is an expanded sectional view along the XX line in FIG. It is a fragmentary perspective view of the turbine rotor blade concerning a prior art.

(First embodiment)
An embodiment of the present invention will be described with reference to FIGS. 1 to 3.

  As shown in FIGS. 1 to 3, a turbine rotor blade 1 according to an embodiment of the present invention is used in a turbine (not shown) of a gas turbine engine such as an aircraft engine or an industrial gas turbine engine. Cooling is possible by using cooling air (a part of the compressed air) CA extracted from a compressor (not shown) or a fan (not shown). And the specific structure of the turbine rotor blade 1 which concerns on embodiment of this invention is as follows.

  That is, the turbine rotor blade 1 is manufactured (molded) by lost wax precision casting, and includes a rotor blade body 3 that obtains a rotational force by a combustion gas G from a combustor (not shown) of a gas turbine engine. ing. Further, a platform 5 is integrally formed on the base end side of the rotor blade body 3, and a dovetail 7 is integrally formed on the platform 5, and the dovetail 7 is a turbine disk (not shown) of the turbine. It can be fitted in a fitting groove (not shown) formed in the peripheral edge.

  A first squealer 11 that allows contact with a stationary component (for example, a shroud) 9 of the turbine is integrally formed on the side of the front surface 3t of the tip surface 3t of the rotor blade body 3, and the tip surface 3t of the rotor blade body 3 is formed. A second squealer 13 that allows contact with the stationary component 9 of the turbine and continues to the first squealer 11 is integrally formed on the back surface 3b side. The first squealer 11 and the second squealer 13 may be discontinuous, or either the first squealer 11 or the second squealer 13 may be omitted.

  From the dovetail 7 to the platform 5, an inlet 15 is formed through which cooling air CA extracted from a compressor or fan can be introduced. Further, a meandering cooling passage 17 into which the cooling air CA can flow is formed inside the rotor blade body 3, and the cooling passage 17 communicates with the introduction port 15.

  A plurality of blow holes 19 through which the cooling air CA can be blown out are formed in the leading edge 3e and the abdominal surface 3v of the moving blade body 3 so as to communicate with the cooling passage 17, and the trailing edge 3p of the moving blade body 3 includes A plurality of discharge holes 21 capable of discharging the cooling air CA are formed in communication with the cooling passage 17. In addition, a plurality of blow holes 19 may be formed on the back surface 3b of the blade main body 3 in addition to the plurality of blow holes 19 formed on the front edge 3e and the abdominal surface 3v of the blade main body 3.

  A first fillet portion 23 having a triangular cross section is integrally formed from the tip surface 3t of the rotor blade body 3 to the tip side of the first squealer 11, and the tip side of the second squealer 13 from the tip surface 3t of the rotor blade body 3 is integrally formed. The second fillet portion 25 having a triangular cross section is integrally formed. In other words, the cross sections of the first squealer 11 and the second squealer 13 have a trapezoidal shape with one oblique side so that the cross-sectional width decreases toward the tip side. Note that either the first fillet portion 23 or the second fillet portion 25 may be omitted.

  A plurality of tip blowout holes 27 through which the cooling air CA can be blown out are formed in the tip surface 3 t of the rotor blade body 3 so as to communicate with the cooling passage 17. A plurality of communication blowout holes 29 through which cooling air CA can be blown out from the abdominal corner 3cv (a part of the inner wall surface of the cooling passage 17) on the inner tip side of the rotor blade body 3 to the outer surface 11s of the first squealer 11 are provided. It is formed along the first fillet portion 23, and the plurality of communication blow holes 29 communicate with the cooling passage 17. The plurality of communication blowout holes 29 may be formed from other locations on the inner wall surface of the cooling passage 17 instead of being formed from the ventral corner 3cv on the inner tip side of the rotor blade body 3.

  Furthermore, a plurality of radiating pin fins (an example of a convex radiating portion) 31 are formed in the ventral corner 3 cv on the inner tip side of the rotor blade body 3. Instead of the plurality of heat radiation pin fins 31 being formed in the abdominal corner 3cv on the inner tip side of the rotor blade body 3, the heat radiation pin fins 31 are formed from different locations on the inner wall surface of the cooling passage 17, or instead of the plurality of heat radiation pin fins 31. In addition, a plurality of heat radiating dimples (an example of a concave heat radiating portion (not shown)) or a plurality of turbulent flow promoting ribs (an example of a convex or concave turbulent flow promoting portion (not shown)) may be formed. It doesn't matter.

  Then, the effect | action and effect of the turbine rotor blade which concern on 1st Embodiment are demonstrated.

  Since the first squealer 11 and the second squealer 13 that allow contact with the stationary part 9 of the turbine are integrally formed on the tip surface 3t of the rotor blade body 3, the first squealer 11 and the second squealer 13 are stationary. The gap between the first squealer 11 and the stationary component 9 of the turbine and the second squealer 13 and the stationary component 9 of the turbine can be set as small as possible close to the component 9. Thereby, during the operation of the gas turbine engine, the clearance flow of the combustion gas G from the abdominal surface 3v side to the back surface 3b side of the rotor blade body 3 can be reduced, and the turbine efficiency of the gas turbine engine can be increased.

  In addition to the above-described operation, the moving blade body 3 can be convectively cooled (internally cooled) from the inside by the cooling air CA flowing into the cooling passage 17 via the inlet 15 during operation of the gas turbine engine. it can. Further, the cooling air CA that has contributed to the convection cooling of the moving blade body 3 is blown out from the plurality of blowing holes 19, the plurality of tip blowing holes 27, and the plurality of communication blowing holes 29, whereby the moving blade body 3, the first Film cooling air that covers the squealer 11 and the second squealer 13 can be formed, and the rotor blade body 3, the first squealer 11, and the second squealer 13 can be film-cooled (externally cooled). A part of the cooling air CA that has contributed to the convection cooling of the rotor blade body 3 is discharged from the plurality of discharge holes 21.

  Here, since the first fillet portion 23 having a triangular cross section is integrally formed from the tip surface 3t of the rotor blade body 3 to the tip side of the first squealer 11, the tip side of the first squealer 11 and the rotor blade body 3 are The heat transfer region between the inner tip surface 3it (in other words, the heat transfer region between the tip side of the first squealer 11 and the cooling passage 17) is increased, and the blade body 3 A sufficient amount of heat transfer to the inner tip surface 3it side can be secured. Similarly, since the second fillet portion 25 having a triangular cross section is integrally formed from the tip surface 3t of the rotor blade body 3 to the tip side of the second squealer 13, the tip side of the second squealer 13 and the rotor blade body 3 are The heat transfer region between the inner tip surface 3it (in other words, the heat transfer region between the tip side of the second squealer 13 and the cooling passage 17) is increased, and the blade body 3 A sufficient amount of heat transfer to the inner tip surface 3it side can be secured. Thereby, during operation of the gas turbine engine, not only film cooling but also convection cooling is used for the first squealer 11 and the second squealer 13 to efficiently cool the first squealer 11 and the second squealer 13. can do.

  In particular, a plurality of heat dissipating pin fins (an example of a convex heat dissipating part) 31 is formed on the ventral corner 3cv on the inner tip side of the rotor blade body 3, and the ventral corner 3cv on the inner tip side of the rotor blade body 3 is formed. A plurality of communication blowing holes 29 are formed from the outer surface 11s of the first squealer 11 to the inner surface of the first squealer 11 while increasing the heat transfer area of the abdominal corner 3cv on the inner tip side of the rotor blade body 3. The convection cooling can be more fully utilized for the first squealer 11.

  Note that, in the turbine rotor blade 1 according to the first embodiment, the first squealer 11 of the first squealer 11 and the second squealer 13 is mainly cooled.

  Therefore, according to the turbine rotor blade 1 according to the first embodiment, not only film cooling but also convection cooling is used for the first squealer 11 and the second squealer 13 during operation of the gas turbine engine. Since the first squealer 11 and the second squealer 13 can be efficiently cooled, the high temperature of the first squealer 11 and the second squealer 13 is sufficiently suppressed, and a part of the first squealer 11 and the second squealer 13 is hot cracked. Alternatively, melting or the like hardly occurs, and the life of the turbine rotor blade 1 can be extended.

(Second Embodiment)
A turbine blade according to a second embodiment will be described with reference to FIG.

  As shown in FIG. 4, the turbine rotor blade 33 according to the second embodiment has a first corner with respect to the span direction of the rotor blade body 3 (the direction from the hub of the rotor blade body 3 toward the tip). Except for the point which inclines to the meat part 23 side, it has the same structure as the turbine rotor blade 1 which concerns on 1st Embodiment.

  And in the turbine blade 33 which concerns on 2nd Embodiment, except the point which utilizes film cooling more fully with respect to the 1st squealer 11, it is the same as the effect | action etc. of the turbine blade 1 which concerns on 1st Embodiment. The effects of the above are exhibited.

(Third embodiment)
A turbine blade according to a third embodiment will be described with reference to FIG.

  As shown in FIG. 5, the turbine rotor blade 35 according to the third embodiment has substantially the same configuration as the turbine rotor blade 33 according to the second embodiment except for the points described below.

  That is, the tip blowout hole 27 is inclined toward the second fillet portion 25 side with respect to the span direction of the rotor blade body 3 instead of being inclined toward the first fillet portion 23 side with respect to the span direction of the rotor blade body 3. ing. Further, instead of forming the plurality of communication blow holes 29 from the abdominal corner 3cv on the inner tip side of the rotor blade body 3 to the outer surface 11s of the first squealer 11, the back corner 3cb on the inner tip side of the rotor blade body 3 is formed. To the outer surface 13 s of the second squealer 13. Further, a plurality of heat radiating pin fins 31 are formed at the dorsal corner 3 cb on the inner tip side of the rotor blade body 3 instead of being formed at the abdominal corner 3 cv on the inner tip side of the rotor blade body 3.

  In the turbine rotor blade 35 according to the third embodiment, the operation of the turbine rotor blade 33 according to the second embodiment (in other words, in the first embodiment), except that the second squealer 13 is mainly cooled. The same effect as that of the turbine rotor blade 1).

(Fourth embodiment)
A turbine blade according to a fourth embodiment will be described with reference to FIG.

  As shown in FIG. 6, the turbine blade 37 according to the fourth embodiment has substantially the same configuration as the turbine blade 33 according to the second embodiment except for the points described below.

  That is, in addition to the plurality of tip blowout holes 27 being inclined toward the first fillet portion 23 with respect to the span direction of the rotor blade body 3, one or more tip blowout holes 27 are formed in the span of the plurality of rotor blade bodies 3. It inclines to the 2nd fillet part 25 side with respect to the direction. Further, in addition to the plurality of communication blowing holes 29 formed from the abdominal side corner 3cv on the inner tip side of the rotor blade body 3 to the outer surface 11s of the first squealer 11, one or more communication blowing holes 29 are provided. 3 from the back corner 3 cb on the inner tip side to the outer surface 13 s of the second squealer 13. Further, a plurality of radiating pin fins 31 are formed in the back corner 3 cb on the inner tip side of the rotor blade body 3 in addition to being formed in the abdominal corner 3 cv on the inner tip side of the rotor blade body 3.

  In the turbine blade 37 according to the fourth embodiment, the operation of the turbine blade 33 according to the second embodiment (in other words, except that the first squealer 11 and the second squealer 13 are equally cooled). The same action as that of the turbine rotor blade 1 according to the first embodiment is exhibited.

(Fifth embodiment)
A turbine rotor blade according to a fifth embodiment will be described with reference to FIGS.

  As shown in FIGS. 7 (a) and 7 (b), the turbine rotor blade 39 according to the fifth embodiment is configured in a shaped type in which each communication blowing hole 29 is expanded toward the outlet side. It has substantially the same configuration as the turbine rotor blade 33 according to the second embodiment. And in the turbine rotor blade 39 which concerns on 5th Embodiment, besides having the effect | action similar to the effect | action etc. of the turbine rotor blade 33 which concerns on 2nd Embodiment, it ejects cooling air CA in a wide range. The cooling efficiency can be increased.

(Sixth embodiment)
A turbine blade according to a sixth embodiment will be described with reference to FIGS. 8 (a), (b), and (c).

  As shown in FIGS. 8 (a), (b), and (c), in the turbine rotor blade 41 according to the sixth embodiment, a plurality of communication blowout holes 29 are arranged in a plurality of rows in a zigzag or lattice shape in the cord direction. Except for this point, it has substantially the same configuration as the turbine rotor blade 33 according to the second embodiment. And in the turbine rotor blade 41 which concerns on 6th Embodiment, by exhibiting the effect | action etc. similar to the effect | action etc. of the turbine rotor blade 33 which concerns on 2nd Embodiment, by increasing the number of the communication blowing holes 29, etc. The area that can be cooled can be increased.

(Seventh embodiment)
A turbine rotor blade according to a seventh embodiment will be described with reference to FIGS.

  As shown in FIGS. 9 (a) and 9 (b), the turbine rotor blade 43 according to the seventh embodiment is the second embodiment except that the positions of the inlets and outlets of the communication blowing holes 29 are shifted in the cord direction. It has substantially the same configuration as the turbine rotor blade 33 according to the embodiment. And in the turbine rotor blade 43 which concerns on 7th Embodiment, besides having the effect | action similar to the effect | action etc. of the turbine rotor blade 33 which concerns on 2nd Embodiment, along a blade surface (mainly abdominal surface 3v). When the flow on the squealer (mainly the first squealer 11) is changed by combining the flow (combustion gas G flow) and the flow passing through the clearance (gap between the turbine rotor blade 43 and the stationary component 9). In addition, the cooling efficiency can be increased by ejecting the cooling air CA in a direction along the flow on the squealer or in a direction crossing the flow on the squealer. Specifically, by blowing out the cooling air CA in a direction along the flow on the squealer, the film cooling air can be made to reach farther and the place away from the communication blowout hole 29 can be cooled. Further, by blowing out the cooling air CA in a direction intersecting with the flow on the squealer, the cooling air CA is blocked by the flow on the squealer and spreads between the communication blow holes 29, and is not easily cooled between the communication blow holes 29. Can be cooled.

  In addition, this invention is not restricted to description of the above-mentioned embodiment, It can implement in a various aspect. Further, the scope of rights encompassed by the present invention is not limited to these embodiments.

CA Cooling Air G Combustion Gas 1 Turbine blade 3 Blade body 3v Abdominal surface 3b Rear surface 3cb Back corner 3cv Abdominal corner 3e Front edge 3it Inner tip surface 3t Tip surface 3t Trailing edge 5 Platform 7 Dovetail 9 Stationary part 11 First skier 11 s outer surface 13 second squealer 13 s outer surface 15 introduction port 17 cooling passage 19 blowout hole 21 discharge hole 23 first fillet part 25 second fillet part 27 tip blowout hole 29 communication blowout hole 31 heat radiation pin fin 33 turbine blade 35 turbine movement Blades 37 Turbine blades 39 Turbine blades 41 Turbine blades 43 Turbine blades 101 Turbine blades 103 Turbine blades 103b Back surfaces 103t Tip surfaces 103v Abdominal surfaces 105 Static parts 107 Squealers 109 Chip outlets 111 Cooling passages

Claims (7)

In turbine blades that are used in gas turbine engine turbines and can be cooled using cooling air,
A rotor blade body that obtains rotational force by combustion gas;
A squealer that is integrally formed on a tip surface of the rotor blade body and allows contact with a stationary component of the turbine,
A cooling passage through which cooling air can flow is formed inside the rotor blade body, and a plurality of outlet holes through which cooling air can be blown out are formed in the blade surface of the rotor blade body so as to communicate with the cooling passage. A fillet portion having a triangular cross section is formed from the tip surface of the blade body to the tip side of the squealer, and a tip blowing hole for blowing cooling air is formed in communication with the cooling passage on the tip surface of the blade body. Turbine blades characterized by   2. The turbine rotor blade according to claim 1, wherein cooling air can be blown out from an inner wall surface of the cooling passage to an outer surface of the squealer and a communication blowout hole is formed.   The turbine blade according to claim 1, wherein the tip blowing hole is inclined with respect to a span direction of the blade main body.   The turbine rotor blade according to any one of claims 1 to 3, wherein a convex or concave heat radiating portion or a turbulent flow promoting portion is formed on an inner wall surface of the cooling passage. .   The turbine rotor blade according to any one of claims 1 to 4, wherein each communication blowout hole is configured in a shaped shape that is expanded toward an outlet side.   5. The turbine operation according to claim 1, wherein the plurality of communication blowout holes are arranged in a plurality of rows in a zigzag pattern or a grid pattern in the cord direction. Wings.   The turbine rotor blade according to any one of claims 1 to 4, wherein the positions of the inlet and outlet of each communication blow hole are shifted in the cord direction.

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