ES2664196T3 - Rotor de compresor supersónico y procedimientos de ensamblaje del mismo - Google Patents

Rotor de compresor supersónico y procedimientos de ensamblaje del mismo Download PDF

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Publication number
ES2664196T3
ES2664196T3 ES11193663.9T ES11193663T ES2664196T3 ES 2664196 T3 ES2664196 T3 ES 2664196T3 ES 11193663 T ES11193663 T ES 11193663T ES 2664196 T3 ES2664196 T3 ES 2664196T3
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Spain
Prior art keywords
flow channel
supersonic
velocity
blades
trailing edge
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.)
Active
Application number
ES11193663.9T
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English (en)
Inventor
Douglas Carl Hofer
Zachary William Nagel
Dhananjaya Rao Gottapu
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General Electric Co
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General Electric Co
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Publication date
Application filed by General Electric Co filed Critical General Electric Co
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Publication of ES2664196T3 publication Critical patent/ES2664196T3/es
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D21/00—Pump involving supersonic speed of pumped fluids
    • 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
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
    • F04D29/284—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors
    • 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
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49229—Prime mover or fluid pump making
    • Y10T29/49236—Fluid pump or compressor making

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

Un rotor de compresor supersónico que comprende: un disco (48) de rotor que comprende un cuerpo que se extiende entre una superficie (56) radialmente interna y una superficie (58) radialmente externa; una pluralidad de álabes (46) acoplados a dicho cuerpo, extendiéndose dichos álabes hacia el exterior de dicho disco (48) de rotor, adyacentes a dichos álabes que forman un par (74) y orientados de manera que un canal de flujo se define entre cada par de alabes adyacentes, extendiéndose dicho canal de flujo entre una abertura (76) de entrada y una abertura (78) de salida, en el que el canal (80) de flujo está dispuesto para canalizar fluido a lo largo de un trayecto (82) de flujo desde la abertura (76) de entrada hasta la abertura (78) de salida en una dirección radial (64); y al menos una rampa (98) de compresión supersónica situada dentro de dicho canal (80) de flujo, estando dicha rampa de compresión supersónica configurada para impedir que se forme una onda de choque normal dentro de dicho canal (80) de flujo y para condicionar un fluido que está siendo canalizado a través de dicho canal de flujo de manera que el fluido está caracterizado por una primera velocidad en dicha abertura de entrada y una segunda velocidad en dicha abertura de salida, siendo cada una de dichas primera velocidad y segunda velocidad supersónicas con respecto a dichas superficies de disco de rotor; en el que dicha rampa (98) de compresión supersónica comprende una superficie (126) de compresión que se extiende entre un borde (130) delantero y un extremo de borde (152) trasero, estando dicho borde delantero situado más próximo a dicha abertura (76) de entrada que dicho borde trasero, definiendo dicho borde trasero una zona (124) de estrangulamiento de dicho canal (80) de flujo, presentando dicha zona de estrangulamiento un área en sección transversal mínima de dicho canal de flujo y en el que dicho borde (152) trasero está situado en posición adyacente a dicha abertura (78) de salida.

Description

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Claims (1)

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ES11193663.9T 2010-12-21 2011-12-15 Rotor de compresor supersónico y procedimientos de ensamblaje del mismo Active ES2664196T3 (es)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US974566 2004-10-27
US12/974,566 US8657571B2 (en) 2010-12-21 2010-12-21 Supersonic compressor rotor and methods for assembling same

Publications (1)

Publication Number Publication Date
ES2664196T3 true ES2664196T3 (es) 2018-04-18

Family

ID=45350680

Family Applications (1)

Application Number Title Priority Date Filing Date
ES11193663.9T Active ES2664196T3 (es) 2010-12-21 2011-12-15 Rotor de compresor supersónico y procedimientos de ensamblaje del mismo

Country Status (7)

Country Link
US (1) US8657571B2 (es)
EP (1) EP2469097B1 (es)
JP (1) JP6088134B2 (es)
CN (1) CN102536854B (es)
ES (1) ES2664196T3 (es)
PL (1) PL2469097T3 (es)
RU (1) RU2588900C2 (es)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9574567B2 (en) * 2013-10-01 2017-02-21 General Electric Company Supersonic compressor and associated method
US9909597B2 (en) 2013-10-15 2018-03-06 Dresser-Rand Company Supersonic compressor with separator

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US2925952A (en) 1953-07-01 1960-02-23 Maschf Augsburg Nuernberg Ag Radial-flow-compressor
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FR2134886A5 (es) * 1971-04-23 1972-12-08 Onera (Off Nat Aerospatiale)
US4408957A (en) * 1972-02-22 1983-10-11 General Motors Corporation Supersonic blading
US4199296A (en) 1974-09-03 1980-04-22 Chair Rory S De Gas turbine engines
US4012166A (en) 1974-12-04 1977-03-15 Deere & Company Supersonic shock wave compressor diffuser with circular arc channels
US4463772A (en) 1981-09-29 1984-08-07 The Boeing Company Flush inlet for supersonic aircraft
US4704861A (en) 1984-05-15 1987-11-10 A/S Kongsberg Vapenfabrikk Apparatus for mounting, and for maintaining running clearance in, a double entry radial compressor
US4620679A (en) 1984-08-02 1986-11-04 United Technologies Corporation Variable-geometry inlet
JPH08121390A (ja) * 1994-10-25 1996-05-14 Ishikawajima Harima Heavy Ind Co Ltd 高速流体用の圧縮機翼形
US5525038A (en) 1994-11-04 1996-06-11 United Technologies Corporation Rotor airfoils to control tip leakage flows
JPH08254156A (ja) * 1995-03-17 1996-10-01 Senshin Zairyo Riyou Gas Jienereeta Kenkyusho:Kk 軸流圧縮機の動翼
US5881758A (en) 1996-03-28 1999-03-16 The Boeing Company Internal compression supersonic engine inlet
JPH11148497A (ja) * 1997-11-17 1999-06-02 Hitachi Ltd 軸流圧縮機動翼
JP2003517525A (ja) 1998-02-26 2003-05-27 アリソン・アドバンスト・ディベロップメント・カンパニー 圧縮機端壁ブリードシステム
DE19812624A1 (de) 1998-03-23 1999-09-30 Bmw Rolls Royce Gmbh Rotor-Schaufelblatt einer Axialströmungsmaschine
US6338609B1 (en) 2000-02-18 2002-01-15 General Electric Company Convex compressor casing
US6488469B1 (en) 2000-10-06 2002-12-03 Pratt & Whitney Canada Corp. Mixed flow and centrifugal compressor for gas turbine engine
US7334990B2 (en) 2002-01-29 2008-02-26 Ramgen Power Systems, Inc. Supersonic compressor
US20030210980A1 (en) * 2002-01-29 2003-11-13 Ramgen Power Systems, Inc. Supersonic compressor
CA2382382A1 (fr) 2002-04-16 2003-10-16 Universite De Sherbrooke Moteur rotatif continu a combustion induite par onde de choc
US7293955B2 (en) 2002-09-26 2007-11-13 Ramgen Power Systrms, Inc. Supersonic gas compressor
US7434400B2 (en) 2002-09-26 2008-10-14 Lawlor Shawn P Gas turbine power plant with supersonic shock compression ramps
US6948306B1 (en) 2002-12-24 2005-09-27 The United States Of America As Represented By The Secretary Of The Navy Apparatus and method of using supersonic combustion heater for hypersonic materials and propulsion testing
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US8960596B2 (en) 2007-08-20 2015-02-24 Kevin Kremeyer Energy-deposition systems, equipment and method for modifying and controlling shock waves and supersonic flow
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US8137054B2 (en) * 2008-12-23 2012-03-20 General Electric Company Supersonic compressor
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US20120156015A1 (en) * 2010-12-17 2012-06-21 Ravindra Gopaldas Devi Supersonic compressor and method of assembling same

Also Published As

Publication number Publication date
EP2469097A2 (en) 2012-06-27
RU2588900C2 (ru) 2016-07-10
CN102536854B (zh) 2016-04-20
PL2469097T3 (pl) 2018-05-30
RU2011151797A (ru) 2013-06-27
EP2469097A3 (en) 2014-10-15
EP2469097B1 (en) 2018-02-21
JP2012132446A (ja) 2012-07-12
US8657571B2 (en) 2014-02-25
US20120156016A1 (en) 2012-06-21
JP6088134B2 (ja) 2017-03-01
CN102536854A (zh) 2012-07-04

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