WO2009093356A1 - タービン翼列エンドウォール - Google Patents
タービン翼列エンドウォール Download PDFInfo
- Publication number
- WO2009093356A1 WO2009093356A1 PCT/JP2008/067326 JP2008067326W WO2009093356A1 WO 2009093356 A1 WO2009093356 A1 WO 2009093356A1 JP 2008067326 W JP2008067326 W JP 2008067326W WO 2009093356 A1 WO2009093356 A1 WO 2009093356A1
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- WO
- WIPO (PCT)
- Prior art keywords
- turbine
- blade
- cax
- pitch
- stationary blade
- Prior art date
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/141—Shape, i.e. outer, aerodynamic form
- F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
- F01D5/143—Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/70—Shape
- F05D2250/71—Shape curved
Definitions
- the present invention relates to a turbine cascade endwall.
- a so-called “cross” is formed from the ventral side of one turbine blade toward the back side of the adjacent turbine blade.
- Flow secondary flow
- the clearance leaked from the gap (tip clearance) between the tip of the turbine rotor blade and the tip end wall of the turbine rotor blade is located downstream of the turbine rotor blade (not shown).
- the inflow angle (incident angle) of the working fluid for example, combustion gas
- a thin solid line in FIG. Is formed and a stagnation point is formed at a position (a position spaced downstream from the front edge of the turbine stationary blade B along the back surface) from the front edge of the turbine stationary blade B to the back side.
- a pressure gradient (pressure distribution) is generated in the blade height direction (vertical direction in FIG. 15) on the rear surface of the turbine stationary blade B.
- the tip side of the turbine stationary blade B as shown by a thin solid line in FIG. A flow from the radially outer side (upper side in FIG. 15) to the hub side (radially inner side: the lower side in FIG. 15) is induced, and a strong hoisting (secondary flow at the rear side) occurs on the rear surface of the turbine vane.
- the solid line arrow in FIG. 15 has shown the flow direction of the working fluid.
- the present invention has been made in view of the above circumstances, and is capable of suppressing the hoisting generated on the back surface of the turbine stationary blade and reducing the secondary flow loss caused by the hoisting.
- the purpose is to provide endwalls.
- the turbine cascade end wall according to the first aspect of the present invention is a turbine cascade end wall located on the tip side of a plurality of turbine stationary blades arranged in an annular shape, and is located upstream of the turbine stationary blade. Is generated in the blade height direction on the rear surface of the turbine stationary blade due to the clearance leakage flow leaking from the gap between the tip of the turbine blade and the tip end wall disposed facing the tip of the turbine blade Pressure gradient relaxation means for relaxing the pressure gradient is provided.
- the turbine blade cascade endwall according to the second aspect of the present invention is a turbine blade cascade endwall located on the tip side of a plurality of turbine stationary blades arranged in an annular shape, and 0% Cax is axially stationary.
- the leading edge position of the blade, 100% Cax is the trailing edge position of the turbine stationary blade in the axial direction
- 0% pitch is the position on the rear surface of the turbine stationary blade
- 100% pitch is the turbine stationary blade facing the abdominal surface of the turbine stationary blade.
- a turbine blade cascade endwall is a turbine blade cascade endwall located on the tip side of a plurality of turbine stationary blades arranged in an annular shape, and 0% Cax is axially stationary.
- the leading edge position of the blade, 100% Cax is the trailing edge position of the turbine stationary blade in the axial direction, 0% pitch is the position on the rear surface of the turbine stationary blade, and 100% pitch is the turbine stationary blade facing the abdominal surface of the turbine stationary blade.
- a turbine blade cascade endwall is a turbine blade cascade endwall located on the tip side of a plurality of turbine stationary blades arranged in an annular shape, and 0% Cax in the axial direction.
- the leading edge position of the blade, 100% Cax is the trailing edge position of the turbine stationary blade in the axial direction
- 0% pitch is the position on the rear surface of the turbine stationary blade
- 100% pitch is the turbine stationary blade facing the abdominal surface of the turbine stationary blade.
- the turbine blade cascade endwall according to the first to fourth aspects of the present invention, it is possible to suppress the hoisting generated on the back surface of the turbine stationary blade, and to reduce the secondary flow loss associated with the hoisting. Can be reduced.
- a turbine according to a fifth aspect of the present invention includes the turbine cascade endwall according to any one of the first to fourth aspects. According to the turbine according to the fifth aspect of the present invention, the turbine blade cascade end that can suppress the hoisting generated on the rear surface of the turbine stationary blade and can reduce the secondary flow loss caused by the hoisting. Since the wall is provided, the performance of the entire turbine can be improved.
- a turbine blade cascade end wall 10 according to the present embodiment includes one turbine stationary blade B and a turbine stationary blade B disposed adjacent to the turbine stationary blade B. Between the blades B, convex portions (pressure gradient relaxing means) 11 are respectively provided.
- a solid line drawn on the chip end wall 10 in FIG. 1 indicates a contour line of the convex portion 11.
- the convex portion 11 is a portion that is gently (smoothly) raised as a whole within a range of approximately ⁇ 30% Cax to + 40% Cax and within a range of approximately 0% pitch to approximately 40% pitch.
- 0% Cax refers to the position of the leading edge of the turbine stationary blade B in the axial direction
- 100% Cax refers to the position of the trailing edge of the turbine stationary blade B in the axial direction.
- -(minus) indicates a position that goes back upstream from the front edge position of the turbine stationary blade B along the axial direction
- + (plus) indicates that the front edge position of the turbine stationary blade B extends along the axial direction. It means the position that went down to the downstream side.
- the 0% pitch refers to the position on the rear surface of the turbine stationary blade B
- the 100% pitch refers to the position on the abdominal surface of the turbine stationary blade B.
- the apex on the front edge side of the convex portion 11 is formed at a position of approximately 30% pitch at a position of approximately ⁇ 20% Cax, and the first ridge line is approximately along the axial direction from this position (substantially parallel). Extends to -30% Cax. Further, the height (convex amount) of the apex on the front edge side of the convex portion 11 is 10% to 20% of the axial cord length of the turbine stationary blade B (the axial length of the turbine stationary blade B) (in this embodiment). About 10%).
- the apex on the rear edge side of the convex portion 11 is formed at a position of approximately 10% pitch at a position of approximately + 20% Cax, and the second ridge line extends substantially along the axial direction from this position (substantially in parallel). It extends to approximately + 40% Cax. Further, the height (convex amount) of the apex on the rear edge side of the convex portion 11 is 10% to 20% of the axial cord length of the turbine stationary blade B (the axial length of the turbine stationary blade B) (in this embodiment). About 10%).
- the center part of the top part of the convex part 11 (namely, area
- the chip end wall 10 for example, streamlines as shown by a thin solid line in FIG. 2 are formed on the chip end wall 10, and the upstream side of the convex portion 11 (in FIG. 1) Lower side) A stagnation point is formed on the surface, and the stagnation is at a position (a position spaced downstream from the front edge of the turbine stationary blade B along the back surface) from the front edge of the turbine stationary blade B to the back side. No dots are formed. Further, the working fluid flowing along the surface of the tip end wall 10 between the back surface of the turbine stationary blade B and the downstream surface (upper side in FIG. 1) of the convex portion 11 is the rear surface of the turbine stationary blade B and the convex portion 11.
- the tip end wall 15 shown in FIGS. 4 to 6 is provided between one turbine vane B and the turbine vane B arranged adjacent to the turbine vane B, as in the first embodiment.
- each has a convex portion 16.
- the solid line drawn on the chip end wall 15 in FIG. 4 indicates the contour lines of the convex portion 16.
- the convex portion 16 is generally smooth (smoothly) within a range of approximately ⁇ 30% Cax to + 10% Cax and within a range of approximately 10% pitch to approximately 50% pitch.
- the apex on the side close to the front edge of the convex portion 16 is formed at a position of about 20% pitch at a position of about ⁇ 10% Cax, and is substantially along the direction orthogonal to the axial direction from this position (substantially parallel).
- the first ridge line extends to a pitch of about 10%.
- the height (convex amount) of the apex on the side close to the front edge of the convex portion 16 is 10% to 20% of the axial cord length of the turbine stationary blade B (the axial length of the turbine stationary blade B). In the embodiment, it is about 10%).
- the apex on the side farther from the front edge of the convex portion 16 is formed at a position of about 40% pitch at a position of about ⁇ 10% Cax, and substantially along the direction perpendicular to the axial direction from this position (substantially). In parallel) the second ridgeline extends to approximately + 50% pitch. Further, the height (convex amount) of the apex on the trailing edge side of the convex portion 16 is 10% to 20% of the axial cord length of the turbine stationary blade B (the axial length of the turbine stationary blade B) (in this embodiment). About 10%).
- the central portion of the top of the convex portion 16 (that is, the region located between the apex on the side close to the front edge and the apex on the side far from the front edge) is located on the side near the front edge and the side far from the front edge.
- the curved surface connects the vertices smoothly.
- the tip end wall 20 includes a recess (pressure gradient relaxation) between one turbine vane B and the turbine vane B disposed adjacent to the turbine vane B. Means) 21.
- a solid line drawn on the chip end wall 20 in FIG. 7 indicates a contour line of the recess 21.
- the concave portion 21 is a portion that is gently (smoothly) depressed generally within a range of approximately ⁇ 50% Cax to + 40% Cax and within a range of approximately 0% pitch to approximately 50% pitch.
- the bottom of the recess 21 is formed at a position of approximately 30% pitch at a position of approximately 0% Cax, and the first valley line is approximately along the axial direction from this position (substantially in parallel). While extending to ⁇ 50% Cax, the second valley line extends from this position substantially along the axial direction (substantially in parallel) to approximately + 40% Cax.
- the depth of the bottom of the recess 21 (the amount of recess) is 10% to 20% (about 10% in the present embodiment) of the axial cord length of the turbine stationary blade B (the axial length of the turbine stationary blade B). ).
- the chip end wall 20 for example, streamlines as shown by a thin solid line in FIG. 8 are formed on the chip end wall 20, and the downstream side of the recess 21 (the upper side in FIG. 7).
- a stagnation point is formed on the surface, and the stagnation point is located at a position (a position spaced downstream from the front edge of the turbine vane B along the back surface) from the front edge of the turbine vane B to the back side. No longer formed.
- the working fluid flowing along the surface of the tip end wall 20 between the rear surface of the turbine vane B and the downstream surface (upper side in FIG. 7) of the recess 21 is downstream of the rear surface of the turbine stator blade B and the recess 21.
- the tip end wall 30 according to the present embodiment has a convex portion (pressure gradient) between one turbine vane B and the turbine vane B arranged adjacent to the turbine vane B. (Relieving means) 31 and recesses (pressure gradient relaxing means) 32 are provided.
- a solid line drawn on the chip end wall 30 in FIG. 10 indicates a contour line of the convex portion 31 and a contour line of the concave portion 32.
- the convex portion 31 is within a range of approximately ⁇ 30% Cax to + 40% Cax, and within a range of approximately 0% pitch to approximately 40% pitch (in the present embodiment, within a range of approximately 0% pitch to approximately 30% pitch). ) In which the entire portion is gently (smoothly) raised.
- the apex on the front edge side of the convex portion 31 is formed at a position of approximately 20% pitch at a position of approximately ⁇ 20% Cax, and the first ridge line is approximately along the axial direction from this position (substantially parallel). Extends to -30% Cax.
- the height (convex amount) of the apex on the front edge side of the convex portion 31 is 10% to 20% of the axial cord length of the turbine stationary blade B (the axial length of the turbine stationary blade B) (in this embodiment). About 10%).
- the apex on the rear edge side of the convex portion 31 is formed at a position of approximately 10% pitch at a position of approximately + 20% Cax, and the second ridge line extends substantially along the axial direction from this position (substantially in parallel). It extends to approximately + 40% Cax. Further, the height (convex amount) of the apex on the rear edge side of the convex portion 31 is 10% to 20% of the axial cord length of the turbine stationary blade B (the axial length of the turbine stationary blade B) (in the present embodiment). About 10%).
- the center part of the top part of the convex part 31 (that is, the region located between the apex on the front edge side and the apex on the rear edge side) is a curved surface that smoothly connects the apex on the front edge side and the apex on the rear edge side.
- the concave portion 32 is a portion that is generally gently (smoothly) depressed within a range of approximately ⁇ 50% Cax to + 40% Cax and within a range of approximately 0% pitch to approximately 50% pitch. It is provided so as to be continuous (connected) to the portion 31. Further, the bottom of the recess 32 is formed at a position of approximately 30% pitch at a position of approximately 0% Cax, and the first valley line is approximately along the axial direction from this position (substantially parallel). While extending to ⁇ 50% Cax, the second valley line extends from this position substantially along the axial direction (substantially in parallel) to approximately + 40% Cax. The depth of the bottom of the recess 32 (the amount of the recess) is 10% to 20% (about 10% in this embodiment) of the axial cord length of the turbine stationary blade B (the axial length of the turbine stationary blade B). ).
- the chip end wall 30 for example, streamlines as shown by a thin solid line in FIG. 11 are formed on the chip end wall 30, and the downstream side of the recess 32 (the upper side in FIG. 10).
- a stagnation point is formed from the surface to the upstream surface (lower side in FIG. 10) of the convex portion 31, and a position (from the front edge of the turbine stationary blade B) that wraps around from the front edge of the turbine stationary blade B A stagnation point is not formed at a position spaced downstream along the back surface.
- the working fluid flowing along the surface of the tip end wall 30 between the rear surface of the turbine vane B and the downstream surface (upper side in FIG.
- the hoisting generated on the back surface of the turbine stationary blade is suppressed, and the secondary flow loss accompanying this hoisting is reduced.
- the performance of the entire turbine will be improved.
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Abstract
Description
タービン性能の向上を図るには、このクロスフローを低減させるとともに、このクロスフローに伴って発生する二次流れ損失を低減させる必要がある。
なお、図15中の実線矢印は、作動流体の流れ方向を示している。
本発明の第1の態様に係るタービン翼列エンドウォールは、環状に配列された複数のタービン静翼のチップ側に位置するタービン翼列エンドウォールであって、前記タービン静翼の上流側に位置するタービン動翼のチップと、このタービン動翼のチップに対向して配置されたチップエンドウォールとの隙間から漏れ出たクリアランス漏れ流れによって、前記タービン静翼の背面において翼高さ方向に発生する圧力勾配を緩和する圧力勾配緩和手段が設けられている。
本発明の第5の態様に係るタービンによれば、タービン静翼の背面に発生する巻き上がりを抑制することができ、この巻き上がりに伴う二次流れ損失を低減させることができるタービン翼列エンドウォールを具備しているので、タービン全体の性能を向上させることができる。
図1に示すように、本実施形態に係るタービン翼列エンドウォール(以下、「チップエンドウォール」という)10は、一のタービン静翼Bと、このタービン静翼Bに隣接配置されたタービン静翼Bとの間に、凸部(圧力勾配緩和手段)11をそれぞれ有するものである。なお、図1中のチップエンドウォール10上に描いた実線は、凸部11の等高線を示している。
ここで、0%Caxとは、軸方向におけるタービン静翼Bの前縁位置のことを指し、100%Caxとは、軸方向におけるタービン静翼Bの後縁位置のことを指している。また、-(マイナス)はタービン静翼Bの前縁位置から軸方向に沿って上流側に遡った位置のことを指し、+(プラス)はタービン静翼Bの前縁位置から軸方向に沿って下流側に下った位置のことを指している。さらに、0%ピッチとは、タービン静翼Bの背面における位置のことを指し、100%ピッチとは、タービン静翼Bの腹面における位置のことを指している。
また、タービン静翼Bの背面と凸部11の下流側(図1において上側)表面との間をチップエンドウォール10の表面に沿って流れる作動流体は、タービン静翼Bの背面と凸部11の下流側表面との間を通過する際に加速され、タービン静翼Bの背面に沿って流れることとなる。
これにより、タービン静翼Bの背面において翼高さ方向(図3において上下方向)に発生する圧力勾配が緩和し、タービン静翼Bの背面上に、例えば、図3中に細い実線で示すような流線を形成させることができ、タービン静翼Bの背面に発生する巻き上がりを抑制することができて、この巻き上がりに伴う二次流れ損失を低減させることができる。
なお、図3中の実線矢印は、作動流体の流れ方向を示している。
凸部16の前縁に近い側の頂点は、略-10%Caxの位置において略20%ピッチの位置に形成されており、この位置から軸方向と直交する方向に略沿って(略平行に)第1の稜線が略10%ピッチのところまで延びている。また、この凸部16の前縁に近い側の頂点の高さ(凸量)は、タービン静翼Bの軸コード長(タービン静翼Bの軸方向長さ)の10%~20%(本実施形態では約10%)とされている。
図7に示すように、本実施形態に係るチップエンドウォール20は、一のタービン静翼Bと、このタービン静翼Bに隣接配置されたタービン静翼Bとの間に、凹部(圧力勾配緩和手段)21をそれぞれ有するものである。なお、図7中のチップエンドウォール20上に描いた実線は、凹部21の等深線を示している。
また、この凹部21の底点は、略0%Caxの位置において略30%ピッチの位置に形成されており、この位置から軸方向に略沿って(略平行に)第1の谷線が略-50%Caxのところまで延びているとともに、この位置から軸方向に略沿って(略平行に)第2の谷線が略+40%Caxのところまで延びている。そして、この凹部21の底点の深さ(凹量)は、タービン静翼Bの軸コード長(タービン静翼Bの軸方向長さ)の10%~20%(本実施形態では約10%)とされている。
また、タービン静翼Bの背面と凹部21の下流側(図7において上側)表面との間をチップエンドウォール20の表面に沿って流れる作動流体は、タービン静翼Bの背面と凹部21の下流側表面との間を通過する際に凹部21内に流れ込むとともに加速され、タービン静翼Bの背面に沿って流れることとなる。
これにより、タービン静翼Bの背面において翼高さ方向(図9において上下方向)に発生する圧力勾配が緩和し、タービン静翼Bの背面上に、例えば、図9中に細い実線で示すような流線を形成させることができ、タービン静翼Bの背面に発生する巻き上がりを抑制することができて、この巻き上がりに伴う二次流れ損失を低減させることができる。
なお、図9中の実線矢印は、作動流体の流れ方向を示している。
図10に示すように、本実施形態に係るチップエンドウォール30は、一のタービン静翼Bと、このタービン静翼Bに隣接配置されたタービン静翼Bとの間に、凸部(圧力勾配緩和手段)31と、凹部(圧力勾配緩和手段)32とをそれぞれ有するものである。なお、図10中のチップエンドウォール30上に描いた実線は、凸部31の等高線および凹部32の等深線を示している。
凸部31の前縁側の頂点は、略-20%Caxの位置において略20%ピッチの位置に形成されており、この位置から軸方向に略沿って(略平行に)第1の稜線が略-30%Caxのところまで延びている。また、この凸部31の前縁側の頂点の高さ(凸量)は、タービン静翼Bの軸コード長(タービン静翼Bの軸方向長さ)の10%~20%(本実施形態では約10%)とされている。
また、この凹部32の底点は、略0%Caxの位置において略30%ピッチの位置に形成されており、この位置から軸方向に略沿って(略平行に)第1の谷線が略-50%Caxのところまで延びているとともに、この位置から軸方向に略沿って(略平行に)第2の谷線が略+40%Caxのところまで延びている。そして、この凹部32の底点の深さ(凹量)は、タービン静翼Bの軸コード長(タービン静翼Bの軸方向長さ)の10%~20%(本実施形態では約10%)とされている。
また、タービン静翼Bの背面と凸部31の下流側(図1において上側)表面との間をチップエンドウォール30の表面に沿って流れる作動流体は、タービン静翼Bの背面と凸部31の下流側表面との間を通過する際に加速され、タービン静翼Bの背面に沿って流れることとなる。
これにより、タービン静翼Bの背面において翼高さ方向(図12において上下方向)に発生する圧力勾配が緩和し、タービン静翼Bの背面上に、例えば、図12中に細い実線で示すような流線を形成させることができ、タービン静翼Bの背面に発生する巻き上がりを抑制することができて、この巻き上がりに伴う二次流れ損失を低減させることができる。
なお、図12中の実線矢印は、作動流体の流れ方向を示している。
Claims (5)
- 環状に配列された複数のタービン静翼のチップ側に位置するタービン翼列エンドウォールであって、
前記タービン静翼の上流側に位置するタービン動翼のチップと、このタービン動翼のチップに対向して配置されたチップエンドウォールとの隙間から漏れ出たクリアランス漏れ流れによって、前記タービン静翼の背面において翼高さ方向に発生する圧力勾配を緩和する圧力勾配緩和手段が設けられていることを特徴とするタービン翼列エンドウォール。 - 環状に配列された複数のタービン静翼のチップ側に位置するタービン翼列エンドウォールであって、
0%Caxを軸方向におけるタービン静翼の前縁位置、100%Caxを軸方向におけるタービン静翼の後縁位置とし、0%ピッチをタービン静翼の背面における位置、100%ピッチを前記タービン静翼の腹面と対向するタービン静翼の腹面における位置とした場合に、
一のタービン静翼と、このタービン静翼に隣接配置された他のタービン静翼との間の、略-50%Cax~+50%Caxの範囲内で、かつ、略0%ピッチ~略50%ピッチの範囲内において、全体的になだらかに***するとともに、軸方向に略平行に延びる凸部が設けられていることを特徴とするタービン翼列エンドウォール。 - 環状に配列された複数のタービン静翼のチップ側に位置するタービン翼列エンドウォールであって、
0%Caxを軸方向におけるタービン静翼の前縁位置、100%Caxを軸方向におけるタービン静翼の後縁位置とし、0%ピッチをタービン静翼の背面における位置、100%ピッチを前記タービン静翼の腹面と対向するタービン静翼の腹面における位置とした場合に、
一のタービン静翼と、このタービン静翼に隣接配置された他のタービン静翼との間の、略-50%Cax~+50%Caxの範囲内で、かつ、略0%ピッチ~略50%ピッチの範囲内において、全体的になだらかに陥没するとともに、軸方向に略平行に延びる凹部が設けられていることを特徴とするタービン翼列エンドウォール。 - 環状に配列された複数のタービン静翼のチップ側に位置するタービン翼列エンドウォールであって、
0%Caxを軸方向におけるタービン静翼の前縁位置、100%Caxを軸方向におけるタービン静翼の後縁位置とし、0%ピッチをタービン静翼の背面における位置、100%ピッチを前記タービン静翼の腹面と対向するタービン静翼の腹面における位置とした場合に、
一のタービン静翼と、このタービン静翼に隣接配置された他のタービン静翼との間の、略-50%Cax~+50%Caxの範囲内で、かつ、略0%ピッチ~略50%ピッチの範囲内において、全体的になだらかに***するとともに、軸方向に略平行に延びる凸部が設けられており、
一のタービン静翼と、このタービン静翼に隣接配置された他のタービン静翼との間の、略-50%Cax~+50%Caxの範囲内で、かつ、略0%ピッチ~略50%ピッチの範囲内において、全体的になだらかに陥没するとともに、軸方向に略平行に延びて前記凸部に連続し前記背面との間に前記凸部を挟むように凹部が設けられていることを特徴とするタービン翼列エンドウォール。 - 請求項1から4のいずれか1項に記載のタービン翼列エンドウォールを備えてなることを特徴とするタービン。
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