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GB689353A - Improvements in centrifugal compressors - Google Patents

Improvements in centrifugal compressors

Info

Publication number
GB689353A
GB689353A GB5668/51A GB566851A GB689353A GB 689353 A GB689353 A GB 689353A GB 5668/51 A GB5668/51 A GB 5668/51A GB 566851 A GB566851 A GB 566851A GB 689353 A GB689353 A GB 689353A
Authority
GB
United Kingdom
Prior art keywords
impeller
decreases
shaft
guide vanes
outlet
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.)
Expired
Application number
GB5668/51A
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.)
Individual
Original Assignee
Individual
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 Individual filed Critical Individual
Publication of GB689353A publication Critical patent/GB689353A/en
Expired legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/54—Reverse-flow combustion chambers
    • 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
    • F02C3/08—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising at least one radial stage
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D17/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
    • F04D17/08—Centrifugal pumps
    • F04D17/10—Centrifugal pumps for compressing or evacuating
    • F04D17/12—Multi-stage pumps
    • F04D17/122—Multi-stage pumps the individual rotor discs being, one for each stage, on a common shaft and axially spaced, e.g. conventional centrifugal multi- stage 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
    • F04D29/40—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
    • F04D29/441—Fluid-guiding means, e.g. diffusers especially adapted for elastic fluid pumps
    • F04D29/444—Bladed diffusers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/50—Inlet or outlet
    • F05D2250/51—Inlet

Landscapes

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

Abstract

689,353. Centrifugal compressors; gas turbine and jet propulsion plant. LYSHOLM, A. March 8, 1951 [March 9, 1950], No. 5668 /51. Classes 110(i) and 110(iii) In a centrifugal compressor, guide vanes ahead of the impeller are shaped so as to impart to the fluid a prewhirl which decreases as the radius decreases, and the outlet edges of the impeller slant towards the axis of rotation of the compressor, so that an increase of head is obtained at the tips of the outlet edges which counteracts the decrease of head due to the prewhirl at the inlet edges. In the jet propulsion plant shown in Fig. 1, the inlet guide vanes 16 are twisted so that the outlet angle is less at the roots than at the tips, so as to impart to the air entering the impeller 10 a prewhirl which decreases as the radius decreases. The impeller 10 and the low-pressure turbine rotor 15 are mounted on a shaft 12, and the high-pressure impeller 11 and the high-pressure turbine rotor 14 are mounted on a shaft 13 the speed of which is preferably onethird greater than that of shaft 12. Most of the compressed air enters a combustion chamber 28 at 30 and 31, adjacent the fuel injection pipe 29, the remainder being supplied for cooling purposes at 32 and 33. Guide vanes 25 may be adjustable. Fig. 4 shows an embodiment in which the outlet angle of the inlet guide vanes 43 decreases to such an extent that it is negative at the roots. To reduce the pressure difference between the root and tip of the outlet edge 44, each impeller blade 42 is shaped to impart to the air a counter-rotation which increases as the radius decreases. Auxiliaries, such as fuel pump, starting motor and controlling devices, may be housed in an annular space 50 and driven through gearing 51 and a shaft 52. Both compressor stages may be driven by a single turbine rotor.
GB5668/51A 1950-03-09 1951-03-08 Improvements in centrifugal compressors Expired GB689353A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
SE689353X 1950-03-09

Publications (1)

Publication Number Publication Date
GB689353A true GB689353A (en) 1953-03-25

Family

ID=20315149

Family Applications (1)

Application Number Title Priority Date Filing Date
GB5668/51A Expired GB689353A (en) 1950-03-09 1951-03-08 Improvements in centrifugal compressors

Country Status (1)

Country Link
GB (1) GB689353A (en)

Cited By (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2947468A (en) * 1957-02-21 1960-08-02 E E Lonabaugh Multi-stage centrifugal compressor
US3088278A (en) * 1957-05-01 1963-05-07 Avco Mfg Corp Gas turbine engine
US3122886A (en) * 1958-09-02 1964-03-03 Davidovitch Vlastimir Gas turbine cycle improvement
US3152443A (en) * 1959-07-17 1964-10-13 United Aircraft Canada Gas turbine powerplant
DE2908774A1 (en) * 1978-03-07 1979-09-13 Kawasaki Heavy Ind Ltd MULTI-STAGE TURBO COMPRESSOR WITH NUMEROUS SHAFTS
FR2419415A1 (en) * 1978-03-07 1979-10-05 Kawasaki Heavy Ind Ltd MULTI-STAGE TURBOCHARGER WITH DIAGONAL FLOW ROTORS
EP0043554A1 (en) * 1980-07-02 1982-01-13 PRATT & WHITNEY AIRCRAFT OF CANADA LIMITED Gas turbine engine
EP0458880A4 (en) * 1989-02-14 1992-02-12 Airflow Research & Manufacturing Corp. Centrifugal fan with airfoil vanes in annular volute envelope
FR2772843A1 (en) * 1997-12-19 1999-06-25 Snecma DEVICE FOR TRANSFERRING FLUID BETWEEN TWO SUCCESSIVE STAGES OF A MULTI-STAGE CENTRIFUGAL TURBOMACHINE
WO2002029252A1 (en) * 2000-10-06 2002-04-11 Pratt & Whitney Canada Corp. Mixed flow and centrifugal compressor for gas turbine engine
GB2395983A (en) * 2002-12-03 2004-06-09 Rolls Royce Plc Mixed flow compressor for gas turbine engine
FR2970508A1 (en) * 2011-01-13 2012-07-20 Turbomeca Bi-centrifugal compressor assembly for turbine engine of helicopter, has compression stage, and diffuser joint that is coupled to compressor stage of centrifugal compressor via air return channel that is inclined upstream
CN102678590A (en) * 2011-03-07 2012-09-19 中国科学院工程热物理研究所 Ultra-compact high-pressure ratio oblique flow-centrifuge combined compressor structure
US20140271173A1 (en) * 2013-03-15 2014-09-18 Rolls-Royce North American Technologies, Inc. Centrifugal compressor with axial impeller exit
CN104613010A (en) * 2014-12-11 2015-05-13 中国北方发动机研究所(天津) Efficient wide-flow compressor
CN104895841A (en) * 2015-04-30 2015-09-09 中国科学院工程热物理研究所 Rectifier, runner structure, combined gas compressor and aviation gas turbine engine
EP3048309A4 (en) * 2013-09-18 2017-04-19 Mitsubishi Heavy Industries, Ltd. Rotating machine
CN112065588A (en) * 2020-09-02 2020-12-11 中国航发沈阳黎明航空发动机有限责任公司 Flow adjusting method of swirl vane type prewhirl nozzle for aircraft engine

Cited By (23)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2947468A (en) * 1957-02-21 1960-08-02 E E Lonabaugh Multi-stage centrifugal compressor
US3088278A (en) * 1957-05-01 1963-05-07 Avco Mfg Corp Gas turbine engine
US3122886A (en) * 1958-09-02 1964-03-03 Davidovitch Vlastimir Gas turbine cycle improvement
US3152443A (en) * 1959-07-17 1964-10-13 United Aircraft Canada Gas turbine powerplant
DE2908774A1 (en) * 1978-03-07 1979-09-13 Kawasaki Heavy Ind Ltd MULTI-STAGE TURBO COMPRESSOR WITH NUMEROUS SHAFTS
FR2419415A1 (en) * 1978-03-07 1979-10-05 Kawasaki Heavy Ind Ltd MULTI-STAGE TURBOCHARGER WITH DIAGONAL FLOW ROTORS
FR2419416A1 (en) * 1978-03-07 1979-10-05 Kawasaki Heavy Ind Ltd MULTI-STAGE, MULTI-SHAFT TURBOCHARGER
EP0043554A1 (en) * 1980-07-02 1982-01-13 PRATT & WHITNEY AIRCRAFT OF CANADA LIMITED Gas turbine engine
EP0458880A4 (en) * 1989-02-14 1992-02-12 Airflow Research & Manufacturing Corp. Centrifugal fan with airfoil vanes in annular volute envelope
FR2772843A1 (en) * 1997-12-19 1999-06-25 Snecma DEVICE FOR TRANSFERRING FLUID BETWEEN TWO SUCCESSIVE STAGES OF A MULTI-STAGE CENTRIFUGAL TURBOMACHINE
WO2002029252A1 (en) * 2000-10-06 2002-04-11 Pratt & Whitney Canada Corp. Mixed flow and centrifugal compressor for gas turbine engine
GB2395983A (en) * 2002-12-03 2004-06-09 Rolls Royce Plc Mixed flow compressor for gas turbine engine
FR2970508A1 (en) * 2011-01-13 2012-07-20 Turbomeca Bi-centrifugal compressor assembly for turbine engine of helicopter, has compression stage, and diffuser joint that is coupled to compressor stage of centrifugal compressor via air return channel that is inclined upstream
CN102678590A (en) * 2011-03-07 2012-09-19 中国科学院工程热物理研究所 Ultra-compact high-pressure ratio oblique flow-centrifuge combined compressor structure
CN102678590B (en) * 2011-03-07 2015-08-12 中国科学院工程热物理研究所 Ultra-compact high pressure ratio oblique flow-centrifugal combined compressor structure
US20140271173A1 (en) * 2013-03-15 2014-09-18 Rolls-Royce North American Technologies, Inc. Centrifugal compressor with axial impeller exit
EP2971787A1 (en) * 2013-03-15 2016-01-20 Rolls-Royce North American Technologies, Inc. Centrifugal compressor with axial impeller exit
EP3048309A4 (en) * 2013-09-18 2017-04-19 Mitsubishi Heavy Industries, Ltd. Rotating machine
CN104613010A (en) * 2014-12-11 2015-05-13 中国北方发动机研究所(天津) Efficient wide-flow compressor
CN104895841A (en) * 2015-04-30 2015-09-09 中国科学院工程热物理研究所 Rectifier, runner structure, combined gas compressor and aviation gas turbine engine
CN104895841B (en) * 2015-04-30 2018-03-23 中国科学院工程热物理研究所 Rectifier, flow passage structure, combined compressor, aero gas turbine engine
CN112065588A (en) * 2020-09-02 2020-12-11 中国航发沈阳黎明航空发动机有限责任公司 Flow adjusting method of swirl vane type prewhirl nozzle for aircraft engine
CN112065588B (en) * 2020-09-02 2021-08-03 中国航发沈阳黎明航空发动机有限责任公司 Flow adjusting method of swirl vane type prewhirl nozzle for aircraft engine

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