WO2015056455A1 - 圧縮機、及びガスタービン - Google Patents
圧縮機、及びガスタービン Download PDFInfo
- Publication number
- WO2015056455A1 WO2015056455A1 PCT/JP2014/052905 JP2014052905W WO2015056455A1 WO 2015056455 A1 WO2015056455 A1 WO 2015056455A1 JP 2014052905 W JP2014052905 W JP 2014052905W WO 2015056455 A1 WO2015056455 A1 WO 2015056455A1
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- WIPO (PCT)
- Prior art keywords
- stationary
- rotor
- blade group
- stationary blade
- blades
- Prior art date
Links
- 230000002093 peripheral effect Effects 0.000 claims abstract description 12
- 238000000605 extraction Methods 0.000 claims description 38
- 239000012530 fluid Substances 0.000 claims description 32
- 239000007789 gas Substances 0.000 claims description 13
- 239000000567 combustion gas Substances 0.000 claims description 6
- 239000000446 fuel Substances 0.000 claims description 5
- 238000009826 distribution Methods 0.000 description 11
- 238000011144 upstream manufacturing Methods 0.000 description 6
- 230000007423 decrease Effects 0.000 description 3
- 238000004519 manufacturing process Methods 0.000 description 2
- 230000003068 static effect Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 1
- 230000010349 pulsation Effects 0.000 description 1
- 238000009827 uniform distribution Methods 0.000 description 1
- 239000013585 weight reducing agent Substances 0.000 description 1
Images
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
- F04D29/666—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by means of rotor construction or layout, e.g. unequal distribution of blades or vanes
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/16—Control of working fluid flow
- F02C9/18—Control of working fluid flow by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages
-
- 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
- F01D17/00—Regulating or controlling by varying flow
- F01D17/10—Final actuators
- F01D17/105—Final actuators by passing part of the fluid
-
- 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
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
-
- 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
- F01D5/02—Blade-carrying members, e.g. rotors
-
- 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
- F01D9/06—Fluid supply conduits to nozzles or the like
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
- F02C3/06—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
- F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
- F02C6/06—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas
- F02C6/08—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas the gas being bled from the gas-turbine compressor
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/541—Specially adapted for elastic fluid pumps
- F04D29/542—Bladed diffusers
- F04D29/544—Blade shapes
-
- 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
-
- 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
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
-
- 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
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/12—Fluid guiding means, e.g. vanes
-
- 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
- F05D2240/00—Components
- F05D2240/20—Rotors
- F05D2240/24—Rotors for turbines
-
- 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
- F05D2260/00—Function
- F05D2260/60—Fluid transfer
- F05D2260/606—Bypassing the fluid
-
- 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
- F05D2260/00—Function
- F05D2260/96—Preventing, counteracting or reducing vibration or noise
- F05D2260/961—Preventing, counteracting or reducing vibration or noise by mistuning rotor blades or stator vanes with irregular interblade spacing, airfoil shape
Definitions
- the present invention relates to a compressor that includes a rotor that rotates about an axis, a casing that surrounds the rotor, and a gas turbine that includes the compressor.
- a compressor that is provided in a gas turbine or the like and includes a rotor that rotates about an axis and a casing that surrounds the rotor from the outer peripheral side, and compresses a fluid such as air.
- Some of the compressors employ a bleed structure for guiding a part of the compressed fluid to the outside of the compressor.
- Patent Document 1 discloses a compressor that employs an extraction structure in which an outer band of a casing is provided with a bleed slot extending in a circumferential direction that reduces energy loss during extraction due to a diffuser effect.
- the bleed structure is provided with a bleed pipe for guiding the fluid bleed from the bleed slot described above through the bleed chamber to the outside of the compressor.
- the extracted fluid has a swirl component in the circumferential direction accompanying the rotation of the rotor. Due to these factors, the flow rate of the fluid increases in the region including the circumferential position where the extraction pipe is provided and on the upstream side of the bleed slot. As a result, it has been confirmed by analysis using CFD (Computational Fluid Dynamics) that the non-uniformity of the circumferential flow distribution is increased in the main flow path.
- CFD Computational Fluid Dynamics
- Such uneven flow distribution may cause pulsation, resulting in stalling near the tip of a moving blade disposed downstream of the bleed slot, and possibly causing a surge in the entire flow of compressed air.
- Such stall and surge may reduce the operating efficiency of the compressor.
- the non-uniformity of the flow rate increases, and the surge margin decreases.
- the possibility of occurrence of a surge increases, which may lead to a reduction in the operating efficiency of the compressor.
- the present invention relates to a compressor capable of suppressing a decrease in operating efficiency by achieving a uniform flow rate of a fluid in a main flow path in the vicinity of a slot for extracting a fluid from the main flow path, and a gas including the compressor Provide a turbine.
- a compressor includes a rotor that rotates about an axis, a rotor casing that surrounds the rotor from an outer peripheral side and defines a main flow path of fluid between the rotor, A plurality of stator blades provided at intervals in the circumferential direction so as to go radially inward from the rotor casing, and provided on the outer peripheral side of the rotor casing and extending in the circumferential direction on the downstream side of the stator blades A bleed chamber casing defining a bleed chamber communicating with the main flow path through a formed slot, and a bleed chamber which is connected to the bleed chamber casing from the outer peripheral side and guides the fluid in the bleed chamber to the inside.
- a pipe formed with an air flow path a plurality of stationary blades located in a region including a circumferential position corresponding to the pipe are defined as a first stationary blade group, and a plurality of stationary blades other than the first stationary blade group are defined as a second stationary blade group.
- first stationary blade group a plurality of stationary blades located in a region including a circumferential position corresponding to the pipe are defined as a first stationary blade group
- second stationary blade group When defined as a blade group, the distance between the radially outer ends of adjacent stationary blades in the first stationary blade group is the distance between the radially outer ends of adjacent stationary blades in the second stationary blade group. It is denser than the interval.
- the first stationary blade group is located in the vicinity of the circumferential position where the pipe is provided, the interval between the radially outer ends of the stationary blade is narrowed at this position. ing. Therefore, at this position, the flow of fluid from the main flow path through the first stationary blade group toward the slot is hindered, and the flow rate of the fluid can be reduced. Therefore, it is possible to suppress an increase in the flow rate of the fluid caused by the rotation of the rotor in the main flow passage in the circumferential position near the slot where the piping is provided, and to achieve a uniform distribution in the circumferential direction of the fluid flow rate. It becomes.
- the plurality of stationary blades are located in a region including a circumferential position corresponding to the piping among the plurality of stationary blades, and the rotor is more than the piping.
- a plurality of stationary blades located in a region including the circumferential position on the first side in the rotational direction may be the first stationary blade group.
- the first stationary blade group has a larger number of stationary blades provided in a predetermined circumferential region than the second stationary blade group.
- the interval between the radially outer ends of the stationary blades may be close.
- stator blades in the first stator blade group By providing more stator blades in the first stator blade group than in the second stator blade group, it is possible to easily close the gap between the radially outer ends of the stator blades. Accordingly, the flow of fluid from the main flow path through the first stationary blade group to the slot is hindered, and it is possible to make the circumferential distribution of the fluid flow rate uniform in the main flow path in the vicinity of the slot.
- At least two stationary blades adjacent to each other in the circumferential direction in the first stationary blade group are provided so as to be close to each other toward the radially outer side.
- the interval between the radially outer ends of the stationary blades may be close.
- the stationary blades of the first stationary blade group are inclined, the distance between the radially outer ends of the stationary blades can be made close without changing the number of stationary blades. Therefore, while facilitating manufacturing, the flow of fluid from the main flow path to the slot through the first stator blade group is prevented, and the circumferential distribution of the fluid flow rate in the main flow path in the vicinity of the slot is made uniform. Can be planned. Moreover, the pressure loss of the fluid which passes a stationary blade does not increase by not changing the quantity of a stationary blade. Therefore, it is possible to make the distribution in the circumferential direction of the fluid flow rate uniform while minimizing the profile loss of the stationary blade.
- the gas turbine burns fuel in the compressed air compressed by the compressor, the compressor compressing air as the fluid by rotating the rotor.
- a combustor that generates combustion gas, and a turbine that is driven by the combustion gas from the combustor.
- the increase in the flow rate of the fluid caused by the rotation of the rotor can be suppressed in the main flow path in the circumferential position near the slot where the piping is provided, by including the compressor.
- the compressor it is possible to make the distribution of the fluid flow rate in the circumferential direction uniform.
- the first stator blade group is provided on the stator blade, and the flow rate of the fluid is made uniform in the main flow channel in the vicinity of the slot for extracting the fluid from the main flow channel. Thereby, it becomes possible to suppress the fall of driving efficiency.
- FIG. 3 is a view of the main flow path and the slot of the compressor according to the first embodiment of the present invention as viewed from the outside in the radial direction, and shows a view taken in the direction of arrow III in FIG. 2.
- FIG. 4 is a view of the compressor according to the first embodiment of the present invention as viewed from the axial direction, and shows a cross-sectional view taken along the line IV-IV in FIG. 2.
- FIG. 3 is a view of the main flow path and the slot of the compressor when the solidity in the stationary blade is constant, as viewed from the radially outer side, and shows an arrow view seen from the same position as the arrow III in FIG. 2.
- the analysis result of the air flow distribution in the main flow path in the vicinity of the slot is shown by color shading.
- FIG. 4 is a view of the compressor according to the second embodiment of the present invention as viewed from the axial direction, and shows a cross-sectional view at the same position as the IV-IV cross section of FIG. 2.
- the gas turbine 200 provided with the compressor 1 is demonstrated.
- the gas turbine 200 combusts by compressing the outside air A0 and generating the compressed air A, and mixing the fuel F supplied from the fuel supply source with the compressed air A and burning it.
- a plurality of combustors 202 that generate the gas G and a turbine 203 that is driven by the combustion gas G are provided.
- the compressed air A is referred to as air A.
- the turbine 203 includes a turbine rotor 204 that rotates about a rotation axis Ar, and a cylindrical casing 205 that covers the turbine rotor 204.
- a main flow path 206 is defined between the turbine rotor 204 and the turbine casing 205.
- the turbine rotor 204 is connected to the rotor 2 in the compressor 1 described later, and rotates about the rotation axis Ar together with the rotor 2.
- the direction in which the rotation axis Ar extends is referred to as an axial direction Da.
- a radial direction based on the rotation axis Ar is defined as a radial direction Dr.
- the side away from the rotation axis Ar in the radial direction Dr is defined as the outside of the radial direction Dr.
- the side approaching the rotation axis Ar in the radial direction Dr is defined as the inner side of the radial direction Dr.
- a circumferential direction based on the rotation axis Ar is defined as a circumferential direction Dc.
- the direction in which the rotor 2 rotates is referred to as a rotation direction R.
- the front side in the rotation direction is a first side R1
- the back side in the rotation direction is a second side R2.
- the plurality of combustors 202 are fixed to the turbine casing 205 at equal intervals in the circumferential direction Dc around the rotation axis Ar.
- the compressor 1 includes a rotor 2 that rotates about a rotation axis Ar and a cylindrical rotor casing 3 that covers the rotor 2.
- the rotor casing 3 defines an annular main flow path 4 through which the compressed air A flows between the rotor casing 3 and the rotor casing 3. Further, the rotor casing 3 has a plurality of stationary blade stages 9 provided on the inner peripheral surface at intervals in the axial direction Da.
- Each stationary blade stage 9 has a plurality of stationary blades 10.
- the plurality of stationary blades 10 are arranged in an annular shape at intervals in the circumferential direction Dc with the rotation axis Ar as a center, and constitute one stationary blade stage 9.
- Each stationary blade 10 extends from the inner peripheral surface of the rotor casing 3 toward the inside in the radial direction Dr.
- the rotor 2 has a rotor body 5 extending in the axial direction Da and a plurality of blade stages 7 fixed to the outer periphery of the rotor body 5 and provided at intervals in the axial direction Da.
- the rotor body 5 is a shaft-like member centered on the rotation axis Ar and extends in the axial direction Da.
- Each blade stage 7 has a plurality of blades 8.
- the plurality of blades 8 are arranged in an annular shape with a space between each other in the circumferential direction Dc with the rotation axis Ar as a center, thereby constituting one blade stage 7.
- Each rotor blade 8 extends from the outer periphery of the rotor body 5 toward the outside in the radial direction Dr.
- One moving blade stage 7 is arranged on the downstream side of one stationary blade stage 9 so that the moving blade stages 7 and the stationary blade stages 9 are alternately arranged.
- the compressor 1 takes the outside air A0 into the main flow path 4 and compresses it in stages by the plurality of stationary blade stages 9 and the plurality of moving blade stages 7 to generate the compressed air A.
- This is a multistage axial compressor.
- the compressor 1 further includes an extraction chamber casing 6 provided on the outer peripheral side of the rotor casing 3 and a plurality of extraction pipes 15 connected to the extraction chamber casing 6.
- the extraction chamber casing 6 is formed in an annular shape around the rotation axis Ar so as to protrude outward from the rotor casing 3 in the radial direction Dr.
- the extraction chamber casing 6 defines an extraction chamber 12 that forms an annular space with the rotor casing 3.
- a slot that extends annularly in the circumferential direction Dc around the rotational axis Ar and communicates the extraction chamber 12 and the main flow path 4. 13 is formed in the rotor casing 3. More specifically, the slot 13 is formed so as to be inclined from the downstream side to the upstream side along the axial direction Da from the inner side in the radial direction Dr of the extraction chamber 12 toward the main flow path 4.
- the extraction pipe 15 is connected to the extraction chamber casing 6 from the outer peripheral side and extends outward in the radial direction Dr. Inside the extraction pipe 15, an extraction passage 14 communicating with the extraction chamber 12 is formed.
- the extraction pipe 15 is connected to the extraction chamber casing 6 with an interval in the circumferential direction Dc.
- the quantity of the extraction pipes 15 varies depending on the model of the compressor 1. In this way, the air A is extracted from the main flow path 4 via the slot 13, the extraction chamber 12, and the extraction piping 15. The extracted air A is guided to the outside of the compressor 1.
- the stationary blade stage 9 will be described in more detail.
- the stationary blade stage 9 provided closest to the slot 13 on the upstream side of the slot 13 is referred to as a stationary blade stage 91.
- a plurality of stationary blades 10 located in a region including the circumferential position Dc corresponding to the extraction pipe 15 are connected to the first stationary blade 10.
- the blade group 101 is assumed.
- a plurality of stationary blades 10 other than the first stationary blade group 101 are defined as a second stationary blade group 102.
- the first stationary blade group 101 is located in a region including the position in the circumferential direction Dc on the first side R1 in the rotation direction R of the rotor body 5 relative to the position in the circumferential direction Dc where the extraction pipe 15 is provided. is doing.
- the distance between the outer ends in the radial direction Dr of the adjacent stator blades 10 is the outer end of the second stator blade group 102 in the radial direction Dr of the adjacent stator blades 10. It is made denser than the distance between each other.
- the number of the stationary blades 10 provided in a predetermined circumferential region is larger in the first stationary blade group 101 than in the second stationary blade group 102. That is, the solidity C / S of the stationary blade 10 is larger in the first stationary blade group 101 than in the second stationary blade group 102.
- the solidity C / S is a value obtained by dividing the dimension in the axial direction Da of the stationary blade 10 by the distance in the circumferential direction Dc between the stationary blades 10 adjacent to each other in the circumferential direction Dc.
- the solidity C / S in the present embodiment indicates a value at the outer end of the stationary blade 10 in the radial direction Dr.
- the first stator blade group 101 is provided in the stator blade stage 91 on the upstream side of the slot 13, so that the first stator blade is located in the vicinity of the position in the circumferential direction Dc where the extraction pipe 15 is provided.
- the group 101 is located, and at this position, the interval between the outer ends of the stationary blade 10 in the radial direction Dr is narrow.
- the first stator blade group 101 is not provided in the stator blade stage 91 and all of them have the same solidity C / S as the second stator blade group 102, that is, the solidity C of the stator blade 10.
- / S is constant is shown.
- the air A has a swirling component, so that a distribution in the circumferential direction Dc occurs in the flow rate of the air A in the main flow path 4 near the slot 13.
- the light-colored portion shown in FIG. 5 is a portion with a small flow rate
- the dark-colored portion is a portion with a large flow rate.
- the phenomenon that the flow rate of the air A increases is confirmed in the vicinity of the position in the circumferential direction Dc where the extraction pipe 15 is provided. Furthermore, the phenomenon in which the flow rate of the air A increases on the first side R1 in the rotation direction R of the rotor 2 and the upstream side in the axial direction Da is remarkable.
- the first stator blade group 101 is provided in a region including the position in the circumferential direction Dc on the first side R1 in the rotation direction R of the rotor 2 relative to the position in the circumferential direction Dc where the extraction pipe 15 is provided.
- the first stator blade group 101 is provided in a region including the position in the circumferential direction Dc on the first side R1 in the rotation direction R of the rotor 2 relative to the position in the circumferential direction Dc where the extraction pipe 15 is provided.
- the flow rate of the air A can be reduced in the region in the circumferential direction Dc where the first stationary blade group 101 is provided. Therefore, it is possible to effectively equalize the distribution in the circumferential direction Dc with respect to the flow rate of the air A in the main flow path 4 in the vicinity of the slot.
- the first stator blade group 101 is provided on the stator blade 10 adjacent to the upstream side of the slot 13, so that the air A in the vicinity of the slot 13 for extracting air from the main flow path 4 is provided. It is possible to make the flow rate uniform. As a result, it is possible to increase the surge margin and suppress a decrease in operating efficiency.
- the main flow path 4 in the vicinity of the slot 13 can be adjusted by adjusting the solidity C / S in the stationary blade stage 91 in this way. It becomes possible to make the flow rate of the air A uniform. Thereby, it becomes possible to suppress the fall of driving efficiency.
- the first stator blade group 101A of the compressor 1A of the present embodiment is different from that of the first embodiment.
- the stator blade 10 is inclined in the circumferential direction Dc toward the outside in the radial direction Dr.
- the stationary blade 10a and the stationary blade 10c located at both ends in the circumferential direction Dc are between them. It inclines so that it may approach to the stationary blade 10b provided in this. Accordingly, the solidity C / S between the stationary blade 10a and the stationary blade 10b and between the stationary blade 10c and the stationary blade 10b is larger than the solidity C / S in the second stationary blade group 102. ing.
- the first vane group 101 ⁇ / b> A is provided with an inclination in the first vane group 101 ⁇ / b> A.
- the interval between the radially outer ends of the matching stationary blades 10 can be reduced. That is, it becomes possible to make the interval between the stationary blades 10 close.
- the pressure loss of the air A passing through the stationary blade 10 does not increase by not changing the quantity of the stationary blade 10 in the first stationary blade group 101A. Therefore, it is possible to reduce the flow rate of air A from the main flow path 4 through the first stationary blade group 101 ⁇ / b> A to the slot 13 while minimizing the profile loss of the stationary blade 10.
- the solidity C / S is increased by the inclination of the two stationary blades 10 in the first stationary blade group 101A.
- at least two stationary blades 10 adjacent to each other in the circumferential direction Dc have a diameter of It is possible to increase the solidity C / S by providing them closer to each other toward the outside of the direction Dr.
- the first stationary blade group 101 (101 ⁇ / b> A) is provided on the first side R ⁇ b> 1 in the rotation direction R with respect to the extraction pipe 15.
- the flow rate of the air A in the main flow path 4 in the vicinity of the slot 13 becomes large even near the position where the extraction pipe 15 is provided on the side other than the first side R1 in the rotation direction R. There is a part.
- the first stationary blade group 101 (101A) may be provided.
- the flow rate of the fluid can be made uniform in the main channel in the vicinity of the slot for extracting air from the main channel. . Thereby, it becomes possible to suppress the fall of driving efficiency.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- Geometry (AREA)
- Fluid Mechanics (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
本願は、2013年10月17日に、日本に出願された特願2013-216696号に基づき優先権を主張し、その内容をここに援用する。
このような不均一な流量分布によって脈動が生じ、ブリードスロットの下流に配置された動翼の先端付近に失速が発生し、圧縮空気の流れ全体にサージが引き起こされる可能性がある。このような失速、及びサージによって圧縮機の運転効率が低下する可能性がある。特に、重量軽減などの目的から抽気配管の数が少なくなっている場合には流量の不均一性が大きくなるため、サージマージンが小さくなる。これにより、サージが発生する可能性が高まり、圧縮機の運転効率の低下を招く可能性がある。
また、静翼の数量を変更しないことで、静翼を通過する流体の圧力損失が増大しない。よって、静翼のプロファイル損失を最小限に抑えつつ、流体流量の周方向分布の均一化を図ることが可能となる。
以下、本発明の実施形態に係る軸流式の圧縮機1について説明する。
まず、圧縮機1を備えるガスタービン200について説明する。
図1に示すように、ガスタービン200は、外気A0を圧縮して圧縮空気Aを生成する圧縮機1と、燃料供給源から供給された燃料Fを圧縮空気Aに混合して燃焼させて燃焼ガスGを生成する複数の燃焼器202と、燃焼ガスGにより駆動するタービン203とを備えている。なお、以下では、圧縮空気Aを空気Aとする。
タービンロータ204は、後述する圧縮機1におけるロータ2に連結され、このロータ2とともに回転軸線Arを中心として回転する。
また、本実施形態において、ロータ2の回転する方向を回転方向Rとする。回転方向Rは、図3に示すとおり、回転方向の手前側を第一側R1とし、回転方向の奥側を第二側R2とする。
図2に示すように、圧縮機1は、回転軸線Arを中心として回転するロータ2と、このロータ2を覆う筒状のロータケーシング3とを備えている。
このように、空気Aは主流路4からスロット13、抽気室12、抽気配管15を経由して抽気される。抽気された空気Aは圧縮機1の外部に導かれる。
静翼段9のうちで、スロット13の上流側で、このスロット13に最も近接して設けられた静翼段9を静翼段91とする。
この第一静翼群101における隣り合う静翼10での径方向Drの外側の端部同士の間隔が、第二静翼群102における隣り合う静翼10での径方向Drの外側の端部同士の間隔よりも密にされている。
ソリディティC/Sとは、静翼10の軸方向Daの寸法を、周方向Dcに隣接する静翼10同士の間の周方向Dcの距離で割った値である。ここで本実施形態でのソリディティC/Sは、静翼10における径方向Drの外側の端部での値を示す。
次に、図6を参照して、本発明の第二実施形態に係る圧縮機1Aについて説明する。
本実施形態の圧縮機1Aは、第一静翼群101Aが第一実施形態とは異なっている。
第一静翼群101Aでは、静翼10が、径方向Drの外側に向かうに従って周方向Dcに傾斜している。
例えば、第一静翼群101(101A)は、抽気配管15よりも回転方向Rの第一側R1に設けられている。しかし、図5の解析結果に示すように、回転方向Rの第一側R1以外における抽気配管15が設けられた位置の近傍でも、スロット13近傍の主流路4内の空気Aの流量が大きくなっている部分がある。このため、この流量が大きくなっている部分に対応する位置、即ち、回転方向Rの第二側R2であって、抽気配管15が設けられた位置に対応する周方向Dcの位置を含む領域に第一静翼群101(101A)が設けられてもよい。
2 ロータ
3 ロータケーシング
4 主流路
5 ロータ本体
6 抽気室ケーシング
7 動翼段
8 動翼
9 静翼段
10、10a、10b、10c 静翼
12 抽気室
13 スロット
14 抽気流路
15 抽気配管
91 静翼段
101、101A 第一静翼群
102 第二静翼群
R 回転方向
R1 回転方向の第一側
R2 回転方向の第二側
Ar 回転軸線
Da 軸方向
Dr 径方向
Dc 周方向
A 空気(圧縮空気、流体)
A0 外気
200 ガスタービン
202 燃焼器
203 タービン
204 タービンロータ
205 タービンケーシング
206 主流路
F 燃料
G 燃焼ガス
Claims (5)
- 軸線回りに回転するロータと、
前記ロータを外周側から囲んで、該ロータとの間に流体の主流路を画成するロータケーシングと、
前記ロータケーシングから径方向内側に向かうように周方向に間隔をあけて設けられた複数の静翼と、
前記ロータケーシングの外周側に設けられて、前記静翼の下流側で周方向に延びて形成されたスロットを介して、前記主流路と連通する抽気室を画成する抽気室ケーシングと、
前記抽気室ケーシングに外周側から接続されて、内側に前記抽気室内の前記流体を外部に導く抽気流路が形成された配管と、
を備え、
前記複数の静翼のうち、前記配管に対応する周方向位置を含む領域に位置する複数の静翼を第一静翼群とし、該第一静翼群以外の複数の静翼を第二静翼群と定義した際に、前記第一静翼群における隣り合う静翼の径方向外側の端部同士の間隔が、前記第二静翼群における隣り合う静翼の径方向外側の端部同士の間隔よりも密にされている圧縮機。 - 前記複数の静翼では、該複数の静翼のうち、前記配管に対応する周方向位置を含む領域に位置し、かつ、前記配管よりも前記ロータの回転方向の第一側の周方向位置を含む領域に位置する複数の静翼を、前記第一静翼群とする請求項1に記載の圧縮機。
- 前記複数の静翼では、前記第一静翼群の方が前記第二静翼群よりも所定の周方向領域に設けられる前記静翼の数量が多くなっていることで、前記静翼の径方向外側の端部同士の間隔が密になっている請求項1又は2に記載の圧縮機。
- 前記複数の静翼では、前記第一静翼群における互いに周方向に隣り合う少なくとも二つの静翼が、径方向外側に向かうに従って互いに近接するように設けられていることで、前記静翼の径方向外側の端部同士の間隔が密になっている請求項1又は2に記載の圧縮機。
- 前記ロータが回転することで前記流体としての空気を圧縮する請求項1から4のいずれか一項に記載の圧縮機と、
前記圧縮機で圧縮された圧縮空気中で燃料を燃焼させて燃焼ガスを生成する燃焼器と、
前記燃焼器からの前記燃焼ガスで駆動するタービンと、
を備えるガスタービン。
Priority Applications (4)
Application Number | Priority Date | Filing Date | Title |
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US14/894,077 US10774750B2 (en) | 2013-10-17 | 2014-02-07 | Compressor with stator vane configuration in vicinity of bleed structure, and gas turbine engine |
EP14854492.7A EP3059456B1 (en) | 2013-10-17 | 2014-02-07 | Compressor and gas turbine |
CN201480029733.6A CN105264237B (zh) | 2013-10-17 | 2014-02-07 | 压缩机及燃气轮机 |
KR1020157033380A KR101798742B1 (ko) | 2013-10-17 | 2014-02-07 | 축류식의 압축기, 및 가스 터빈 |
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JP2013-216696 | 2013-10-17 | ||
JP2013216696A JP6134628B2 (ja) | 2013-10-17 | 2013-10-17 | 軸流式の圧縮機、及びガスタービン |
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PCT/JP2014/052905 WO2015056455A1 (ja) | 2013-10-17 | 2014-02-07 | 圧縮機、及びガスタービン |
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US (1) | US10774750B2 (ja) |
EP (1) | EP3059456B1 (ja) |
JP (1) | JP6134628B2 (ja) |
KR (1) | KR101798742B1 (ja) |
CN (1) | CN105264237B (ja) |
WO (1) | WO2015056455A1 (ja) |
Cited By (2)
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JP2017166482A (ja) * | 2016-03-15 | 2017-09-21 | ゼネラル・エレクトリック・カンパニイ | 不均一なベーン間隔 |
DE102017200754A1 (de) | 2017-01-18 | 2018-07-19 | Siemens Aktiengesellschaft | Einströmleitgitter, Einströmungsanordnung, Turbomaschine |
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JP6037996B2 (ja) | 2013-10-17 | 2016-12-07 | 三菱重工業株式会社 | 圧縮機、及びガスタービン |
KR20170017062A (ko) | 2015-08-05 | 2017-02-15 | 두산중공업 주식회사 | 가스터빈 압축기 |
DE102018212176A1 (de) | 2018-07-23 | 2020-01-23 | MTU Aero Engines AG | Hochdruckverdichter für ein Triebwerk |
CN115917119B (zh) * | 2020-09-28 | 2024-06-07 | 三菱重工业株式会社 | 蒸汽涡轮 |
US11828226B2 (en) * | 2022-04-13 | 2023-11-28 | General Electric Company | Compressor bleed air channels having a pattern of vortex generators |
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Also Published As
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CN105264237B (zh) | 2017-05-31 |
JP6134628B2 (ja) | 2017-05-24 |
US10774750B2 (en) | 2020-09-15 |
CN105264237A (zh) | 2016-01-20 |
EP3059456A1 (en) | 2016-08-24 |
EP3059456A4 (en) | 2017-06-21 |
JP2015078662A (ja) | 2015-04-23 |
KR20160021097A (ko) | 2016-02-24 |
EP3059456B1 (en) | 2018-10-31 |
US20160123236A1 (en) | 2016-05-05 |
KR101798742B1 (ko) | 2017-11-16 |
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