US20080101922A1 - Asymmetric compressor air extraction method - Google Patents

Asymmetric compressor air extraction method Download PDF

Info

Publication number
US20080101922A1
US20080101922A1 US11/588,389 US58838906A US2008101922A1 US 20080101922 A1 US20080101922 A1 US 20080101922A1 US 58838906 A US58838906 A US 58838906A US 2008101922 A1 US2008101922 A1 US 2008101922A1
Authority
US
United States
Prior art keywords
extraction
compressor
casing
holes
rotating stall
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Abandoned
Application number
US11/588,389
Inventor
Steven Mark Schirle
Donald Kasperski
Nick Martin
Robert M. Zacharias
Timothy E. Dejoris
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Co
Original Assignee
General Electric Co
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by General Electric Co filed Critical General Electric Co
Priority to US11/588,389 priority Critical patent/US20080101922A1/en
Assigned to GENERAL ELECTRIC COMPANY reassignment GENERAL ELECTRIC COMPANY ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: SCHIRLE, STEVEN MARK, MARTIN, NICK, DEJORIS, TIMOTHY E., KASPERSKI, DONALD, ZACHARIAS, ROBERT M.
Priority to KR1020070107902A priority patent/KR20080038041A/en
Priority to JP2007277085A priority patent/JP2008111435A/en
Priority to DE102007051633A priority patent/DE102007051633A1/en
Priority to CNA2007101817876A priority patent/CN101169137A/en
Publication of US20080101922A1 publication Critical patent/US20080101922A1/en
Abandoned legal-status Critical Current

Links

Images

Classifications

    • 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
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/44—Fluid-guiding means, e.g. diffusers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/02—Surge control
    • F04D27/0207—Surge control by bleeding, bypassing or recycling fluids
    • F04D27/0215—Arrangements therefor, e.g. bleed or by-pass valves
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/02—Surge control
    • F04D27/0207—Surge control by bleeding, bypassing or recycling fluids
    • F04D27/0223—Control schemes therefor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/02—Surge control
    • F04D27/0207—Surge control by bleeding, bypassing or recycling fluids
    • F04D27/023—Details or means for fluid extraction
    • 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
    • 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
    • F04D29/545—Ducts

Definitions

  • Power generation industrial axial flow gas turbines are designed to optimally operate at a fixed rotational speed and output.
  • traditional axial flow industrial gas turbine compressors have limited variable stage geometry and air extractions. These three factors, fixed speed operation, limited variable stage geometry and limited extractions lead to significant off-design aerodynamic conditions during start-up and shutdown operations. Rotating stall occurs in axial flow compressors during these off-design operations.
  • Rotating stall manifests itself as local stall cells that rotate at about half the wheel speed. These cells provide coherent unsteady aerodynamic loads on both the rotor and stator blades. As the rotor changes speed, the stall cell count changes thereby setting up different nodal diameters. The vibratory response on the rotor and stator blades from the rotating stall aerodynamic loads may lead to increased sensitivity of normal blade damage and premature failures.
  • the invention improves axial flow compressor rotor and stator blade durability by eliminating or reducing the coherent aerodynamic forces created by rotating stall. More specifically, the invention provides a method to mistune the rotating stall aerodynamics thereby preventing the formation of coherent unsteady loads.
  • the invention may be embodied in a method of controlling air flow in a compressor comprising: flow disturbances created by part speed or off-design operation; extracting flow at a series of circumferentially asymmetric spaced positions at chosen axial portions of the compressor, thereby creating an extraction pattern to act against flow disturbances.
  • the invention may also be embodied in a method of controlling air flow in a compressor comprising: actuating extraction of compressor air, asymmetrically about a circumference of said compressor casing to act against a disturbance such as rotating stall.
  • FIG. 1 is a schematic representation of rotating stall.
  • FIG. 2 is a schematic representation of asymmetric compressor air extraction as an example embodiment of the invention.
  • FIG. 3 is a schematic perspective view of a compressor adapted for asymmetric compressor air extraction in accordance with an example embodiment of the invention.
  • Power generation industrial axial flow gas turbines are designed to optimally operate at a fixed rotational speed and output.
  • traditional axial flow industrial gas turbine compressors have limited variable stage geometry and air extractions. These three factors lead to significant off-design aerodynamic conditions during start-up and shutdown operations. Rotating stall can occur in axial flow compressors during these off-design operations.
  • Rotating stall manifests itself as local stall cells 10 that rotate at about half the wheel speed ( ⁇ stall cells ⁇ 1 ⁇ 2 ⁇ engine ). These stall cells provide coherent unsteady aerodynamic loads on both the rotor and stator blades 12 . As the rotor changes speed, the stall cell count changes thereby setting up different excitation characteristics known as nodal diameters. The vibratory response on the rotor and stator blades from the rotating stall aerodynamic loads may lead to increased sensitivity to normal blade damage and premature failures.
  • Improved axial flow compressor blade durability results from eliminating or reducing the coherent aerodynamic forces created by rotating stall. Reduction in these aerodynamic vibratory loads increases blade damage tolerance to normal operation damage such as tip rubs, corrosion and leading edge foreign object damage.
  • This invention improves axial flow compressor rotor and stator blade durability by eliminating or reducing the aerodynamic excitation on axial flow compressor rotor and stator blades from rotating stall. More specifically, the invention provides a method to mistune the rotating stall aerodynamics by preventing the formation of coherent unsteady loads.
  • a novel manner of eliminating or reducing disturbances such as rotating stall in compressors is proposed, e.g., at a series of circumferentially spaced positions at one or more a chosen axial positions (stage) compressor air is selectively bled asymmetrically, in a circumferentially selective manner dependent upon the origin of the variations, to act against the rotating stall flow disturbances.
  • the air extraction process would be initiated, that is to say a rotating stall condition or potential stall condition would be countered by asymmetric extraction of air.
  • No sensors are required as this is an operationally identified phenomenon—part speed and/or part load.
  • compressor air is extracted through a series of generally shaped holes or slots 16 on the outer diameter flow path wall 18 in an asymmetric circumferential pattern.
  • the extraction pattern is determined as a function of the rotating stall nodal diameter pattern as well as the aerodynamic strength of the cells.
  • the asymmetric multi-stage bleed pattern disrupts the rotating stall cell rotational pattern, preventing the formation of a coherent aerodynamic excitation.
  • FIG. 3 schematically illustrates an axial flow compressor equipped with generally shaped air extraction holes or slots in accordance with an example embodiment of the invention.
  • Generally shaped extraction holes or slots 16 are defined to selectively bleed compressor air through the compressor casing.
  • the inlets are corrected by conduits (not shown) through respective fast acting shut-off valves (not shown) for removing the extracted air and re-routing it as deemed necessary or desirable.
  • similar air extraction holes are provided at a number of axial stations, the circumferentially corresponding extraction conduits at two or more stations may share the same control valve.
  • a circumferential series of extraction holes or slots are to be simultaneously actuated in ordinary course a circumferential series of extraction conduits may be connected to a common control valve.
  • control unit should close the valve(s) once the stall cell has been suppressed.
  • the extraction is continued for a predetermined period and then terminated.
  • the extraction is gradually reduced after it is initiated.
  • Other extraction protocols may be adopted as deemed necessary or desirable.
  • the invention provides an assembly wherein compressor air is extracted through a series of generally shaped holes or slots 16 on the outer diameter flow path wall 18 in an asymmetric circumferential pattern as the illustrated by way of example in FIG. 2 .
  • the extraction pattern may be experimentally or analytically determined as a function of the rotating stall nodal diameter pattern as well as the aerodynamic strength of the cells. These extractions may be located at a single, axial location or at several axial locations depending on the nature of the rotating stall, the required extraction flow and engine configuration restrictions. As can be seen in FIG. 3 , this example embodiment presents an asymmetric extraction layout with two axial locations.
  • the number of axial positions, circumferential arc lengths, extraction hole shape and number are defined based on the nature of the rotating stall.
  • the asymmetric multi-stage bleed pattern disrupts the rotating stall cell rotational pattern, preventing the formation of a coherent aerodynamic excitation as conceptually illustrated in FIG. 2 .
  • the asymmetric bleed features include, at each specified axial location 20 on the compressor case 18 , asymmetrically spaced extractions 16 , within a specified arc length ⁇ arc at specified circumferential locations with defined extraction shapes, to provide the required total extraction flow.
  • the arc length ⁇ arc is about 90 degrees.
  • the extractions 16 are placed on the top half case, thereby providing for easier field retrofit as well as improved accessibility for extraction manifolds and piping (not illustrated).
  • the multi-stage extractions would require an extraction manifold to route the flow away from the unit.
  • the invention can provide the following benefits: 1) reduce/eliminate coherent unsteady aerodynamic excitation on blades; 2) retrofitable to existing engines with split case designs; 3) enabler for advanced aerodynamic blades; 4) improves compressor blade durability by increasing damage tolerance to tip rubs, corrosion pits and leading edge damage.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Sustainable Development (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

A method to mistune rotating stall aerodynamics by preventing the formation of coherent unsteady loads. Compressor air is extracted in an asymmetric circumferential pattern. The asymmetric bleed pattern disrupts the rotating stall cell rotational pattern, preventing the formation of a coherent aerodynamic excitation.

Description

    BACKGROUND OF THE INVENTION
  • Power generation industrial axial flow gas turbines are designed to optimally operate at a fixed rotational speed and output. In addition, traditional axial flow industrial gas turbine compressors have limited variable stage geometry and air extractions. These three factors, fixed speed operation, limited variable stage geometry and limited extractions lead to significant off-design aerodynamic conditions during start-up and shutdown operations. Rotating stall occurs in axial flow compressors during these off-design operations.
  • Rotating stall manifests itself as local stall cells that rotate at about half the wheel speed. These cells provide coherent unsteady aerodynamic loads on both the rotor and stator blades. As the rotor changes speed, the stall cell count changes thereby setting up different nodal diameters. The vibratory response on the rotor and stator blades from the rotating stall aerodynamic loads may lead to increased sensitivity of normal blade damage and premature failures.
    • BRIEF DESCRIPTION OF THE INVENTION
  • The invention improves axial flow compressor rotor and stator blade durability by eliminating or reducing the coherent aerodynamic forces created by rotating stall. More specifically, the invention provides a method to mistune the rotating stall aerodynamics thereby preventing the formation of coherent unsteady loads.
  • The invention may be embodied in a method of controlling air flow in a compressor comprising: flow disturbances created by part speed or off-design operation; extracting flow at a series of circumferentially asymmetric spaced positions at chosen axial portions of the compressor, thereby creating an extraction pattern to act against flow disturbances.
  • The invention may also be embodied in a method of controlling air flow in a compressor comprising: actuating extraction of compressor air, asymmetrically about a circumference of said compressor casing to act against a disturbance such as rotating stall.
    • BRIEF DESCRIPTION OF THE DRAWINGS
  • FIG. 1 is a schematic representation of rotating stall.
  • FIG. 2 is a schematic representation of asymmetric compressor air extraction as an example embodiment of the invention; and
  • FIG. 3 is a schematic perspective view of a compressor adapted for asymmetric compressor air extraction in accordance with an example embodiment of the invention.
    •  DETAILED DESCRIPTION OF THE INVENTION
  • Power generation industrial axial flow gas turbines are designed to optimally operate at a fixed rotational speed and output. In addition, traditional axial flow industrial gas turbine compressors have limited variable stage geometry and air extractions. These three factors lead to significant off-design aerodynamic conditions during start-up and shutdown operations. Rotating stall can occur in axial flow compressors during these off-design operations.
  • Rotating stall, schematically presented in FIG. 1, manifests itself as local stall cells 10 that rotate at about half the wheel speed (ωstall cells≈½ ωengine). These stall cells provide coherent unsteady aerodynamic loads on both the rotor and stator blades 12. As the rotor changes speed, the stall cell count changes thereby setting up different excitation characteristics known as nodal diameters. The vibratory response on the rotor and stator blades from the rotating stall aerodynamic loads may lead to increased sensitivity to normal blade damage and premature failures.
  • Improved axial flow compressor blade durability results from eliminating or reducing the coherent aerodynamic forces created by rotating stall. Reduction in these aerodynamic vibratory loads increases blade damage tolerance to normal operation damage such as tip rubs, corrosion and leading edge foreign object damage.
  • This invention improves axial flow compressor rotor and stator blade durability by eliminating or reducing the aerodynamic excitation on axial flow compressor rotor and stator blades from rotating stall. More specifically, the invention provides a method to mistune the rotating stall aerodynamics by preventing the formation of coherent unsteady loads.
  • Thus and more specifically, a novel manner of eliminating or reducing disturbances such as rotating stall in compressors is proposed, e.g., at a series of circumferentially spaced positions at one or more a chosen axial positions (stage) compressor air is selectively bled asymmetrically, in a circumferentially selective manner dependent upon the origin of the variations, to act against the rotating stall flow disturbances. In such a case, the air extraction process would be initiated, that is to say a rotating stall condition or potential stall condition would be countered by asymmetric extraction of air. No sensors are required as this is an operationally identified phenomenon—part speed and/or part load.
  • In an example embodiment of the invention, as schematically illustrated in FIGS. 2 and 3, compressor air is extracted through a series of generally shaped holes or slots 16 on the outer diameter flow path wall 18 in an asymmetric circumferential pattern. The extraction pattern is determined as a function of the rotating stall nodal diameter pattern as well as the aerodynamic strength of the cells. The asymmetric multi-stage bleed pattern disrupts the rotating stall cell rotational pattern, preventing the formation of a coherent aerodynamic excitation.
  • FIG. 3 schematically illustrates an axial flow compressor equipped with generally shaped air extraction holes or slots in accordance with an example embodiment of the invention. Generally shaped extraction holes or slots 16 are defined to selectively bleed compressor air through the compressor casing. The inlets are corrected by conduits (not shown) through respective fast acting shut-off valves (not shown) for removing the extracted air and re-routing it as deemed necessary or desirable. If similar air extraction holes are provided at a number of axial stations, the circumferentially corresponding extraction conduits at two or more stations may share the same control valve. If a circumferential series of extraction holes or slots are to be simultaneously actuated in ordinary course a circumferential series of extraction conduits may be connected to a common control valve. To economize on the extraction of high pressure air, the control unit should close the valve(s) once the stall cell has been suppressed. In one example embodiment, the extraction is continued for a predetermined period and then terminated. In another example embodiment, the extraction is gradually reduced after it is initiated. Other extraction protocols may be adopted as deemed necessary or desirable.
  • As mentioned above, to prevent the formation of coherent unsteady loads and thereby mistune the rotating stall aerodynamics, the invention provides an assembly wherein compressor air is extracted through a series of generally shaped holes or slots 16 on the outer diameter flow path wall 18 in an asymmetric circumferential pattern as the illustrated by way of example in FIG. 2. The extraction pattern may be experimentally or analytically determined as a function of the rotating stall nodal diameter pattern as well as the aerodynamic strength of the cells. These extractions may be located at a single, axial location or at several axial locations depending on the nature of the rotating stall, the required extraction flow and engine configuration restrictions. As can be seen in FIG. 3, this example embodiment presents an asymmetric extraction layout with two axial locations. The number of axial positions, circumferential arc lengths, extraction hole shape and number are defined based on the nature of the rotating stall. The asymmetric multi-stage bleed pattern disrupts the rotating stall cell rotational pattern, preventing the formation of a coherent aerodynamic excitation as conceptually illustrated in FIG. 2.
  • As is understood from the foregoing, the asymmetric bleed features include, at each specified axial location 20 on the compressor case 18, asymmetrically spaced extractions 16, within a specified arc length θarc at specified circumferential locations with defined extraction shapes, to provide the required total extraction flow. In an example embodiment, the arc length θarc is about 90 degrees.
  • For a split case application, the extractions 16 are placed on the top half case, thereby providing for easier field retrofit as well as improved accessibility for extraction manifolds and piping (not illustrated). As understood from the foregoing, the multi-stage extractions would require an extraction manifold to route the flow away from the unit.
  • Thus, the invention can provide the following benefits: 1) reduce/eliminate coherent unsteady aerodynamic excitation on blades; 2) retrofitable to existing engines with split case designs; 3) enabler for advanced aerodynamic blades; 4) improves compressor blade durability by increasing damage tolerance to tip rubs, corrosion pits and leading edge damage.
  • While the invention has been described in connection with what is presently considered to be the most practical and preferred embodiment, it is to be understood that the invention is not to be limited to the disclosed embodiment, but on the contrary, is intended to cover various modifications and equivalent arrangements included within the spirit and scope of the appended claims.

Claims (14)

1. A method of controlling air flow in a compressor comprising:
extracting high pressure air from a vicinity of or downstream of the chosen axial portion through a casing of the compressor, in a circumferentially asymmetric pattern to act against flow disturbances such as rotating stall.
2. A method as in claim 1, wherein said extraction of high pressure air is through a plurality of holes or slots disposed asymmetrically about the circumference of the casing of the compressor.
3. A method as in claim 1, wherein said casing is a split casing, and wherein said extraction of high pressure air is through a plurality of holes or slots disposed in a top casing part of said split casing.
4. A method as in claim 1, comprising extracting high pressure air through a plurality of holes or slots disposed in an arc defined by the required flow volume and nature of the rotating stall formation.
5. A method as in claim 4, wherein said holes or slots are asymmetrically disposed in said arc.
6. A method as in claim 1, wherein said extraction is terminated after a predetermined period.
7. A method as in claim 1, wherein said extraction may be gradually reduced after it is initiated.
8. A method of controlling air flow in a compressor comprising: actuating extraction of compressor air, asymmetrically about a circumference of said compressor casing to act against a disturbance such as rotating stall.
9. A method as in claim 8, wherein said extraction of high pressure air is through a plurality of holes or slots disposed asymmetrically about the circumference of the casing of the compressor.
10. A method as in claim 8, wherein said casing is a split casing, and wherein said extraction of high pressure air is through a plurality of holes or slots disposed in a top casing part of said split casing.
11. A method as in claim 8, comprising extracting high pressure air through a plurality of holes or slots disposed in an arc defined by the required flow volume and nature of the rotating stall formation.
12. A method as in claim 11, wherein said holes or slots are asymmetrically disposed in said arc.
13. A method as in claim 8, wherein said extraction is terminated after a predetermined period.
14. A method as in claim 8, wherein said extraction may be gradually reduced after it is initiated.
US11/588,389 2006-10-27 2006-10-27 Asymmetric compressor air extraction method Abandoned US20080101922A1 (en)

Priority Applications (5)

Application Number Priority Date Filing Date Title
US11/588,389 US20080101922A1 (en) 2006-10-27 2006-10-27 Asymmetric compressor air extraction method
KR1020070107902A KR20080038041A (en) 2006-10-27 2007-10-25 Asymmetric compressor air extraction method
JP2007277085A JP2008111435A (en) 2006-10-27 2007-10-25 Asymmetric compressor air extraction method
DE102007051633A DE102007051633A1 (en) 2006-10-27 2007-10-26 Compressor controlling method for industrial axial gas turbine of power station, involves extracting highly compressed air in proximity or downstream of selected axial section by housing of compressor in asymmetrical sample
CNA2007101817876A CN101169137A (en) 2006-10-27 2007-10-29 Asymmetric compressor air extraction method

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US11/588,389 US20080101922A1 (en) 2006-10-27 2006-10-27 Asymmetric compressor air extraction method

Publications (1)

Publication Number Publication Date
US20080101922A1 true US20080101922A1 (en) 2008-05-01

Family

ID=39244627

Family Applications (1)

Application Number Title Priority Date Filing Date
US11/588,389 Abandoned US20080101922A1 (en) 2006-10-27 2006-10-27 Asymmetric compressor air extraction method

Country Status (5)

Country Link
US (1) US20080101922A1 (en)
JP (1) JP2008111435A (en)
KR (1) KR20080038041A (en)
CN (1) CN101169137A (en)
DE (1) DE102007051633A1 (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20110274537A1 (en) * 2010-05-09 2011-11-10 Loc Quang Duong Blade excitation reduction method and arrangement
WO2012091216A1 (en) * 2010-12-30 2012-07-05 한국항공우주연구원 Axial flow compressor and method for fluid stabilization control thereof
WO2014052967A1 (en) * 2012-09-28 2014-04-03 United Technologies Corporation Case assembly for a gas turbine engine
US11635030B2 (en) 2017-06-13 2023-04-25 General Electric Company Compressor bleed apparatus for a turbine engine

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP6037996B2 (en) * 2013-10-17 2016-12-07 三菱重工業株式会社 Compressor and gas turbine

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4196472A (en) * 1977-09-09 1980-04-01 Calspan Corporation Stall control apparatus for axial flow compressors
US5340271A (en) * 1990-08-18 1994-08-23 Rolls-Royce Plc Flow control method and means
US5462403A (en) * 1994-03-21 1995-10-31 United Technologies Corporation Compressor stator vane assembly
US5984625A (en) * 1996-10-15 1999-11-16 California Institute Of Technology Actuator bandwidth and rate limit reduction for control of compressor rotating stall
US6098010A (en) * 1997-11-20 2000-08-01 The Regents Of The University Of California Method and apparatus for predicting and stabilizing compressor stall
US6409469B1 (en) * 2000-11-21 2002-06-25 Pratt & Whitney Canada Corp. Fan-stator interaction tone reduction
US6506010B1 (en) * 2001-04-17 2003-01-14 General Electric Company Method and apparatus for compressor control and operation in industrial gas turbines using stall precursors

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4196472A (en) * 1977-09-09 1980-04-01 Calspan Corporation Stall control apparatus for axial flow compressors
US5340271A (en) * 1990-08-18 1994-08-23 Rolls-Royce Plc Flow control method and means
US5462403A (en) * 1994-03-21 1995-10-31 United Technologies Corporation Compressor stator vane assembly
US5984625A (en) * 1996-10-15 1999-11-16 California Institute Of Technology Actuator bandwidth and rate limit reduction for control of compressor rotating stall
US6098010A (en) * 1997-11-20 2000-08-01 The Regents Of The University Of California Method and apparatus for predicting and stabilizing compressor stall
US6409469B1 (en) * 2000-11-21 2002-06-25 Pratt & Whitney Canada Corp. Fan-stator interaction tone reduction
US6506010B1 (en) * 2001-04-17 2003-01-14 General Electric Company Method and apparatus for compressor control and operation in industrial gas turbines using stall precursors

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20110274537A1 (en) * 2010-05-09 2011-11-10 Loc Quang Duong Blade excitation reduction method and arrangement
WO2012091216A1 (en) * 2010-12-30 2012-07-05 한국항공우주연구원 Axial flow compressor and method for fluid stabilization control thereof
US9334869B2 (en) 2010-12-30 2016-05-10 Korea Aerospace Research Institute Axial compressor and control method thereof to stabilize fluid
WO2014052967A1 (en) * 2012-09-28 2014-04-03 United Technologies Corporation Case assembly for a gas turbine engine
US11635030B2 (en) 2017-06-13 2023-04-25 General Electric Company Compressor bleed apparatus for a turbine engine

Also Published As

Publication number Publication date
JP2008111435A (en) 2008-05-15
CN101169137A (en) 2008-04-30
KR20080038041A (en) 2008-05-02
DE102007051633A1 (en) 2008-04-30

Similar Documents

Publication Publication Date Title
US8123471B2 (en) Variable stator vane contoured button
US6905303B2 (en) Methods and apparatus for assembling gas turbine engines
CN102220881B (en) Turbocharger with axial turbine and parallel flow compressor
EP2636868B1 (en) Turbine housing for twin scroll turbocharger
US20100260591A1 (en) Spanwise split variable guide vane and related method
EP1696113B1 (en) Bolt-on radial bleed manifold
CN205349788U (en) A axial compressor end wall is handled for controlling wherein leakage stream
CN102220900B (en) Turbosupercharger
US20170284297A1 (en) Translating inlet for adjusting airflow distortion in gas turbine engine
US8974175B2 (en) Turbomachine compressor
CA2567940C (en) Methods and apparatuses for gas turbine engines
US20170284304A1 (en) Valved airflow passage assembly for adjusting airflow distortion in gas turbine engine
CN104421199A (en) Functionally asymmetric two-sided turbocharger wheel and diffuser
CN108799200B (en) Compressor installation with discharge channel and auxiliary flange
CN105736460B (en) Axial compressor rotor incorporating non-axisymmetric hub flowpath and splitter blades
CN108799202B (en) Compressor installation with discharge channel comprising a baffle
EP2554793B1 (en) Inter-turbine ducts with guide vanes of a gas turbine engine
US20080101922A1 (en) Asymmetric compressor air extraction method
EP2472127A2 (en) Axial compressor
US8591184B2 (en) Hub flowpath contour
US8628297B2 (en) Tip flowpath contour
EP3112608B1 (en) Turbocharger system and control method
WO2010002294A1 (en) A vane for a gas turbine component, a gas turbine component and a gas turbine engine
EP3392468A1 (en) Exhaust diffuser of a gas turbine engine having variable guide vane rings
EP2778346B1 (en) Rotor for a gas turbine engine, corresponding gas turbine engine and method of improving gas turbine engine rotor efficiency

Legal Events

Date Code Title Description
AS Assignment

Owner name: GENERAL ELECTRIC COMPANY, NEW YORK

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:SCHIRLE, STEVEN MARK;KASPERSKI, DONALD;MARTIN, NICK;AND OTHERS;REEL/FRAME:018470/0621;SIGNING DATES FROM 20061003 TO 20061023

STCB Information on status: application discontinuation

Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION