US20110271654A1 - Diffuser for gas turbine system - Google Patents

Diffuser for gas turbine system Download PDF

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Publication number
US20110271654A1
US20110271654A1 US12/774,262 US77426210A US2011271654A1 US 20110271654 A1 US20110271654 A1 US 20110271654A1 US 77426210 A US77426210 A US 77426210A US 2011271654 A1 US2011271654 A1 US 2011271654A1
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US
United States
Prior art keywords
diffuser
gas flow
generally
ducts
flow
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
US12/774,262
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English (en)
Inventor
Gunnar Leif Siden
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 US12/774,262 priority Critical patent/US20110271654A1/en
Assigned to GENERAL ELECTRIC COMPANY reassignment GENERAL ELECTRIC COMPANY ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: SIDEN, GUNNAR LEIF
Assigned to GENERAL ELECTRIC COMPANY reassignment GENERAL ELECTRIC COMPANY ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: SIDEN, GUNNAR LEIF
Priority to JP2011094586A priority patent/JP2011236897A/ja
Priority to EP11164824.2A priority patent/EP2385219A3/en
Priority to CN2011101251499A priority patent/CN102235387A/zh
Publication of US20110271654A1 publication Critical patent/US20110271654A1/en
Abandoned legal-status Critical Current

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Classifications

    • 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
    • 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
    • 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
    • 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
    • F05D2260/00—Function
    • F05D2260/60—Fluid transfer

Definitions

  • the subject matter disclosed herein related generally to gas turbine systems, and more particularly to diffusers in gas turbine systems.
  • a conventional gas turbine system includes a compressor section, a combustor section, and at least one turbine section.
  • the compressor section is configured to compress air as the air flows through the compressor section.
  • the air is then flowed from the compressor section to the combustor section, where it is mixed with fuel and combusted, generating a hot gas flow.
  • the hot gas flow is provided to the turbine section, which utilizes the hot gas flow by extracting energy from it to power the compressor, an electrical generator, and other various loads.
  • typical known compressor sections include an axial diffuser 19 , as shown in FIG. 2 , which acts to reduce the velocity of the air flow exiting the compressor section.
  • known diffusers typically diffuse the air flow as the air flow travels along a generally longitudinal axis 90 of the gas turbine system.
  • the air flow exiting the compressor section generally has an “exit swirl” component, meaning that the air flow is traveling in a generally rotational direction, with tangential and radial flow components, along with traveling in a generally longitudinal direction.
  • a guide vane or guide vanes 28 are typically disposed upstream of the axial diffuser 19 in the compressor section. The guide vanes 28 are designed to reduce the exit swirl.
  • a diffuser that reduces air flow pressure drops would be desired in the art. Additionally, a diffuser that utilizes the exit swirl associated with the air flow to guide the air flow to the combustor section would be advantageous. Further, a diffuser that eliminates the need for guide vanes in the compressor section would be desired.
  • a diffuser for a gas turbine system having a longitudinal axis includes a plurality of diffuser ducts.
  • Each of the plurality of diffuser ducts is disposed annularly about the longitudinal axis and has an inlet, an outlet, and a passage extending between the inlet and the outlet.
  • the outlet of each of the plurality of diffuser ducts is tangentially offset from the inlet of the respective diffuser duct.
  • Each of the plurality of diffuser ducts is configured to flow a gas flow therethrough, reducing the gas flow velocity.
  • FIG. 1 is a schematic view of a gas turbine system of the present disclosure
  • FIG. 2 is a cross-sectional view of a known gas turbine system
  • FIG. 3 is an exploded perspective view of one embodiment of a diffuser of the present disclosure
  • FIG. 4 is a perspective view of one embodiment of a diffuser duct of the present disclosure.
  • FIG. 5 is a front view of one embodiment of a diffuser of the present disclosure.
  • FIG. 6 is a front view of another embodiment of a diffuser of the present disclosure.
  • FIG. 1 is a schematic diagram of a gas turbine system 10 .
  • the system 10 may include a compressor section 12 , a combustor section 14 , and a turbine section 16 . Further, the system 10 may include a plurality of compressor sections 12 , combustor sections 14 , and turbine sections 16 .
  • the compressor section 12 and turbine section 16 may be coupled by a shaft 18 .
  • the shaft 18 may be a single shaft or a plurality of shaft segments coupled together to form shaft 18 .
  • the gas turbine system 10 may have a central longitudinal axis 90 . For example, the shaft 18 may be disposed longitudinally along the axis 90 .
  • the compressor section 12 may compress a gas flow 80 as the gas flow 80 flows through the compressor section 12 .
  • the gas flow 80 may be, for example, air or any other suitable gas.
  • the compressor section 12 may then flow the gas flow 80 to the combustor section 14 , which may be configured to accept the gas flow 80 , as discussed below.
  • the gas flow 80 may flow in a generally longitudinal direction with respect to the longitudinal axis 90 .
  • the gas flow 80 may generally further include other flow components.
  • the gas flow 80 after being compressed may have flow components known collectively in the art as an “exit swirl.”
  • the gas flow 80 may flow in a generally tangential direction, and may further flow in a generally radial direction.
  • the compressor section 12 may include at least one guide vane 28 .
  • the guide vane 28 may reduce the exit swirl, thus reducing the tangential and radial flow components of the gas flow 80 .
  • the compressor section 12 may be free from guide vanes 28 .
  • the compressor section 12 may include a diffuser 20 .
  • the diffuser 20 may be configured to reduce the velocity of the gas flow 80 , as discussed below.
  • the diffuser 20 may further generally flow the gas flow 80 to the combustor section 14 .
  • gas flow 80 may flow through the diffuser 20 and be provided to the combustor section 14 .
  • the gas flow 80 may exit the diffuser 20 into a plenum 22 .
  • the gas flow 80 may then be provided from the plenum 22 to the combustor section 14 .
  • the gas flow 80 may exit the diffuser 20 directly into the combustor section 14 .
  • the combustor section 14 may include a plurality of combustor cans 24 .
  • the diffuser 20 may comprise a plurality of diffuser ducts 30 .
  • Each of the diffuser ducts 30 may be coupled with a combustor can 24 .
  • the combustor cans 24 may be configured to accept gas flow 80 from one of the plurality of diffuser ducts 30 .
  • each of the combustor cans 24 may be fluidly connected to one of the diffuser ducts 30 , such that gas flow 80 exiting the diffuser ducts 30 immediately enters the combustor cans 24 , and thus the combustor section 14 .
  • the diffuser 20 of the present disclosure includes a plurality of diffuser ducts 30 .
  • each of the plurality of diffuser ducts 30 may have an inlet 32 , an outlet 36 , and a passage extending between the inlet 32 and the outlet 36 .
  • the diffuser ducts 30 may be configured to flow a gas flow 80 therethrough, reducing the gas flow 80 velocity.
  • the inlet 32 of each of the plurality of diffuser ducts 30 may have a cross-sectional area that is generally smaller than the cross-sectional area of the outlet 36 of the respective diffuser duct 30 .
  • the inlets 32 and outlets 36 may have generally circular or oval cross-sections, rectangular cross-sections, triangular cross-sections, or any other suitable polygonal cross-sections. Further, it should be understood that the inlet 32 and outlet 34 of a respective diffuser duct 30 need not have similarly shaped cross-sections. For example, in one embodiment, the inlet 32 may have a generally rectangular cross-section, while the outlet 36 may have a generally circular cross-section.
  • the passage 34 may be generally tapered between the inlet 32 and the outlet 36 .
  • the passage 34 may be generally conically shaped.
  • the passage 34 may have a generally rectangular cross-section, triangular cross-section, or any other suitable polygonal cross-section. It should be understood that the cross-sectional shape of the passage 34 may change throughout the passage 34 as the passage 34 tapers from the relatively smaller inlet 32 to the relatively larger outlet 36 .
  • the diffuser ducts 30 may be disposed in an annular array about the longitudinal axis 90 .
  • the gas flow 80 may flow through the inlets 32 into the annular array of diffuser ducts 30 .
  • the outlet 36 of each of the plurality of diffuser ducts 30 may be offset from the inlet 32 of the respective diffuser duct 30 .
  • offset means spaced from along the identified coordinate direction.
  • the outlet 36 of each of the plurality of diffuser ducts 30 may be tangentially offset from the inlet 32 of the respective diffuser duct 30 , such as offset along a tangential axis 92 . Because the outlet 36 of each of the plurality of diffuser ducts 30 is tangentially offset from the inlet 32 of the respective diffuser duct 30 , the diffuser ducts 30 may advantageously utilize the tangential component of the gas flow 80 exit swirl to flow the gas flow 80 through the diffuser duets 30 .
  • this utilization of the tangential gas flow 80 component may eliminate the need for guide vanes 28 in the compressor section 12 . Further, the utilization of the tangential gas flow 80 component may prevent gas flow 80 pressure losses due to flow direction changes in typical prior art gas turbine systems as the gas flow 80 flows from the compressor section 12 through the diffuser 20 to the combustor section 14 .
  • the outlet 36 of each of the plurality of diffuser ducts 30 may be longitudinally offset from the inlet 32 of the respective diffuser duct 30 , such as offset along the longitudinal axis 90 . Because the outlet 36 of each of the plurality of diffuser ducts 30 is longitudinally offset from the inlet 32 of the respective diffuser duct 30 , the diffuser ducts 30 may advantageously utilize the longitudinal component of the gas flow 80 to flow the gas flow 80 through the diffuser ducts 30 .
  • the outlet 36 of each of the plurality of diffuser ducts 30 may be radially offset from the inlet 32 of the respective diffuser duct 30 , such as offset along a radial axis 94 . Because the outlet 36 of each of the plurality of diffuser ducts 30 is radially offset from the inlet 32 of the respective diffuser duct 30 , the diffuser ducts 30 may advantageously utilize the radial component of the gas flow 80 exit swirl to flow the gas flow 80 through the diffuser ducts 30 .
  • the tangential axis 92 and the radial axis 94 are defined individually for each diffuser duct 30 with respect to the circumference defined by the diffuser 20 and diffuser ducts 30 , as shown in FIGS. 5 and 6 , and that the axes 92 and 94 vary for each diffuser duct 30 about the circumference of the diffuser 20 based on the number of diffuser ducts 30 disposed in an annular array about the longitudinal axis 90 of the diffuser 20 .
  • Each of the passages 34 may include a first guide portion 40 , as shown in FIG. 4 .
  • the first guide portion 40 may be disposed adjacent the inlet 32 of the respective diffuser duct 30 .
  • the first guide portion 40 may be any portion of the passage 34 of the diffuser duct 30 .
  • the first guide portion 40 may be that portion of the passage 34 that redirects the general direction of gas flow 80 within a diffuser duct 30 .
  • the first guide portions 40 may be configured to guide the gas flow 80 from a generally longitudinal flow direction to a generally tangential flow direction.
  • the first guide portions 40 may be configured to guide the gas flow 80 from a generally longitudinal flow direction to a generally radial flow direction, a generally tangential and radial flow direction, a generally tangential and longitudinal flow direction, or to a generally tangential, radial, and longitudinal flow direction.
  • gas flow 80 in any general direction, such as in a generally longitudinal direction may have other flow components, such as radial and tangential flow components, and is not limited to flow strictly in the referenced direction.
  • the gas flow 80 may continue to flow through the passage 34 towards the outlet 36 .
  • the passages 34 may extend in a generally linear manner downstream of the guide portion 40 with respect to the gas flow 80 , as shown in FIG. 6 .
  • the gas flow 80 after passing through the first guide portion 40 of the passage 34 , may continue through the passage 34 in a generally linear manner.
  • the passages 34 may extend in a generally curvilinear manner downstream of the guide portion 40 with respect to the gas flow 80 , as shown in FIGS. 3 through 5 .
  • the gas flow 80 after passing through the first guide portion 40 of the passage 34 , may continue through the passage 34 in a generally curvilinear manner.
  • Each of the passages 34 may further include a second guide portion 42 .
  • the second guide portion 42 may be disposed adjacent the outlet 36 of the respective diffuser duct 30 .
  • the second guide portion 42 may be any portion of the passage 34 of the diffuser duct 30 .
  • the second guide portion 42 may be another portion of the passage 34 that further redirects the general direction of gas flow 80 within a diffuser duct 30 .
  • the second guide portions 42 may be configured to guide the gas flow 80 from a generally tangential flow direction to a generally longitudinal flow direction.
  • the second guide portions 42 may be configured to guide the gas flow 80 from a generally radial flow direction, a generally tangential and radial flow direction, a generally tangential and longitudinal flow direction, or a generally tangential, radial, and longitudinal flow direction to a generally longitudinal flow direction.
  • gas flow 80 in any general direction, such as in a generally longitudinal direction may have other flow components, such as radial and tangential flow components, and is not limited to flow strictly in the referenced direction.
  • the gas flow 80 may flow through the passage 34 towards the guide portion 42 and the outlet 36 .
  • the passages 34 may extend in a generally linear manner upstream of the second guide portion 42 with respect to the gas flow 80 , as shown in FIG. 6 .
  • the gas flow 80 before passing through the second guide portion 42 of the passage 34 , may travel through the passage 34 in a generally linear manner.
  • the passages 34 may extend in a generally curvilinear manner upstream of the second guide portion 42 with respect to the gas flow 80 , as shown in FIGS. 3 through 5 .
  • the gas flow 80 before passing through the second guide portion 42 of the passage 34 , may travel through the passage 34 in a generally curvilinear manner.
  • the gas flow 80 may exit the diffuser 20 .
  • the gas flow 80 may exit the diffuser 20 flowing in a generally tangential direction. It should be understood, however, that the gas flow 80 may have radial and longitudinal flow components, and is not limited to flow in a strictly tangential direction.
  • the gas flow 80 may exit the diffuser 20 flowing in a generally longitudinal direction. It should be understood, however, that the gas flow 80 may have tangential and radial flow components, and is not limited to flow in a strictly longitudinal direction. Further, the gas flow 80 may exit the diffuser 20 flowing in a generally radial direction. It should be understood, however, that the gas flow 80 may have tangential and longitudinal flow components, and is not limited to flow in a strictly radial direction.
  • the gas flow 80 may enter a plenum 22 , or may directly enter the combustor section 14 .
  • each of the diffuser ducts 30 may be coupled to a combustor can 24 , and the gas flow 80 exiting each diffuser duct 30 may enter the combustor can 24 coupled with the diffuser duct 30 .
  • the diffuser 20 may include a number of diffuser ducts 20 equal to the number of combustor cans 24 in the combustor 14 .
  • the diffuser 20 in various embodiments, may include 8, 12, or 16 diffuser ducts 30 , or any other suitable number of diffuser ducts 30 .

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US12/774,262 2010-05-05 2010-05-05 Diffuser for gas turbine system Abandoned US20110271654A1 (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
US12/774,262 US20110271654A1 (en) 2010-05-05 2010-05-05 Diffuser for gas turbine system
JP2011094586A JP2011236897A (ja) 2010-05-05 2011-04-21 ガスタービンシステム用のディフューザ
EP11164824.2A EP2385219A3 (en) 2010-05-05 2011-05-04 Diffuser for gas turbine system between compressor exit and combustor inlet
CN2011101251499A CN102235387A (zh) 2010-05-05 2011-05-05 用于燃气涡轮系统的扩散器

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US12/774,262 US20110271654A1 (en) 2010-05-05 2010-05-05 Diffuser for gas turbine system

Publications (1)

Publication Number Publication Date
US20110271654A1 true US20110271654A1 (en) 2011-11-10

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US12/774,262 Abandoned US20110271654A1 (en) 2010-05-05 2010-05-05 Diffuser for gas turbine system

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US (1) US20110271654A1 (ja)
EP (1) EP2385219A3 (ja)
JP (1) JP2011236897A (ja)
CN (1) CN102235387A (ja)

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20130224007A1 (en) * 2012-02-29 2013-08-29 Jose L. Rodriguez Mid-section of a can-annular gas turbine engine to introduce a radial velocity component into an air flow discharged from a compressor of the mid-section
US20130224009A1 (en) * 2012-02-29 2013-08-29 David A. Little Mid-section of a can-annular gas turbine engine with a radial air flow discharged from the compressor section
US9528392B2 (en) 2013-05-10 2016-12-27 General Electric Company System for supporting a turbine nozzle
US9777746B2 (en) 2013-09-03 2017-10-03 Dresser-Rand Company Motor cooling system manifold
US20190170353A1 (en) * 2016-04-25 2019-06-06 Mitsubishi Heavy Industries, Ltd. Compressor diffuser and gas turbine
US20190323519A1 (en) * 2018-04-18 2019-10-24 Mitsubishi Heavy Industries, Ltd. Compressor diffuser and gas turbine
US10550853B2 (en) 2015-12-25 2020-02-04 Kawasaki Jukogyo Kabushiki Kaisha Gas turbine engine
US20200049161A1 (en) * 2018-08-10 2020-02-13 Pratt & Whitney Canada Corp. Compressor diffuser with diffuser pipes varying in natural vibration frequencies
US11098650B2 (en) 2018-08-10 2021-08-24 Pratt & Whitney Canada Corp. Compressor diffuser with diffuser pipes having aero-dampers

Citations (4)

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Publication number Priority date Publication date Assignee Title
US2475911A (en) * 1944-03-16 1949-07-12 Power Jets Res & Dev Ltd Combustion apparatus
US2582809A (en) * 1944-12-30 1952-01-15 Power Jets Res & Dev Ltd Air and fuel regulating means in internal-combustion turbine power plants
US4527386A (en) * 1983-02-28 1985-07-09 United Technologies Corporation Diffuser for gas turbine engine
US20100031663A1 (en) * 2007-08-13 2010-02-11 Snecma Turbomachine with a diffuser

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US3333762A (en) * 1966-11-16 1967-08-01 United Aircraft Canada Diffuser for centrifugal compressor
US3489340A (en) * 1968-04-16 1970-01-13 Garrett Corp Centrifugal compressor
DE2436458A1 (de) * 1973-08-17 1975-02-20 Int Harvester Co Kreiselverdichter
US5131142A (en) * 1990-10-30 1992-07-21 Carrier Corporation Method of making pipe diffuser structure
US6123506A (en) * 1999-01-20 2000-09-26 Pratt & Whitney Canada Corp. Diffuser pipe assembly
US7156618B2 (en) * 2004-11-17 2007-01-02 Pratt & Whitney Canada Corp. Low cost diffuser assembly for gas turbine engine
US8038392B2 (en) * 2007-07-18 2011-10-18 Honda Motor Co., Ltd. Axial diffuser for a centrifugal compressor

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2475911A (en) * 1944-03-16 1949-07-12 Power Jets Res & Dev Ltd Combustion apparatus
US2582809A (en) * 1944-12-30 1952-01-15 Power Jets Res & Dev Ltd Air and fuel regulating means in internal-combustion turbine power plants
US4527386A (en) * 1983-02-28 1985-07-09 United Technologies Corporation Diffuser for gas turbine engine
US20100031663A1 (en) * 2007-08-13 2010-02-11 Snecma Turbomachine with a diffuser

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20130224009A1 (en) * 2012-02-29 2013-08-29 David A. Little Mid-section of a can-annular gas turbine engine with a radial air flow discharged from the compressor section
US9476355B2 (en) * 2012-02-29 2016-10-25 Siemens Energy, Inc. Mid-section of a can-annular gas turbine engine with a radial air flow discharged from the compressor section
US10012098B2 (en) * 2012-02-29 2018-07-03 Siemens Energy, Inc. Mid-section of a can-annular gas turbine engine to introduce a radial velocity component into an air flow discharged from a compressor of the mid-section
US20130224007A1 (en) * 2012-02-29 2013-08-29 Jose L. Rodriguez Mid-section of a can-annular gas turbine engine to introduce a radial velocity component into an air flow discharged from a compressor of the mid-section
US9528392B2 (en) 2013-05-10 2016-12-27 General Electric Company System for supporting a turbine nozzle
US9777746B2 (en) 2013-09-03 2017-10-03 Dresser-Rand Company Motor cooling system manifold
US10550853B2 (en) 2015-12-25 2020-02-04 Kawasaki Jukogyo Kabushiki Kaisha Gas turbine engine
US20190170353A1 (en) * 2016-04-25 2019-06-06 Mitsubishi Heavy Industries, Ltd. Compressor diffuser and gas turbine
US11060726B2 (en) * 2016-04-25 2021-07-13 Mitsubishi Heavy Industries, Ltd. Compressor diffuser and gas turbine
US20190323519A1 (en) * 2018-04-18 2019-10-24 Mitsubishi Heavy Industries, Ltd. Compressor diffuser and gas turbine
US20200049161A1 (en) * 2018-08-10 2020-02-13 Pratt & Whitney Canada Corp. Compressor diffuser with diffuser pipes varying in natural vibration frequencies
US10823196B2 (en) * 2018-08-10 2020-11-03 Pratt & Whitney Canada Corp. Compressor diffuser with diffuser pipes varying in natural vibration frequencies
US11098650B2 (en) 2018-08-10 2021-08-24 Pratt & Whitney Canada Corp. Compressor diffuser with diffuser pipes having aero-dampers

Also Published As

Publication number Publication date
EP2385219A3 (en) 2013-06-05
EP2385219A2 (en) 2011-11-09
CN102235387A (zh) 2011-11-09
JP2011236897A (ja) 2011-11-24

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Effective date: 20100504

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Effective date: 20110413

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