GB1256119A - Turbine engine compressor - Google Patents

Turbine engine compressor

Info

Publication number
GB1256119A
GB1256119A GB52279/69A GB5227969A GB1256119A GB 1256119 A GB1256119 A GB 1256119A GB 52279/69 A GB52279/69 A GB 52279/69A GB 5227969 A GB5227969 A GB 5227969A GB 1256119 A GB1256119 A GB 1256119A
Authority
GB
United Kingdom
Prior art keywords
blades
turbine engine
axial
centrifugal
engine compressor
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
GB52279/69A
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.)
Pratt and Whitney Canada Corp
Original Assignee
United Aircraft of Canada Ltd
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 United Aircraft of Canada Ltd filed Critical United Aircraft of Canada Ltd
Publication of GB1256119A publication Critical patent/GB1256119A/en
Expired legal-status Critical Current

Links

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
    • F04D17/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
    • F04D17/08—Centrifugal pumps
    • F04D17/10—Centrifugal pumps for compressing or evacuating
    • 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
    • F04D29/285—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors the compressor wheel comprising a pair of rotatable bladed hub portions axially aligned and clamped together
    • 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
    • F04D29/30—Vanes

Landscapes

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

Abstract

1,256,119. Centrifugal and axial-flow compressors. UNITED AIRCRAFT OF CANADA Ltd. Oct.24, 1969 [Nov.21, 1968], No.52279/69. Heading F1C. A compressor for compressing fluid at supersonic velocity in a gas turbine engine, comprises a rotor having a set of axial-flow blades 22 arranged upstream of and circumferentiallystaggered relative to, a set of centrifugal main blades 26 interdigitated with splitter blades 28. The blades 22, 26, 28 are jointly rotatable at the same speed. The axial spacing between the trailing edges of blades 22 and the leading edges of blades 26 is preferably between one half and one inch.
GB52279/69A 1968-11-21 1969-10-24 Turbine engine compressor Expired GB1256119A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US77768268A 1968-11-21 1968-11-21

Publications (1)

Publication Number Publication Date
GB1256119A true GB1256119A (en) 1971-12-08

Family

ID=25110948

Family Applications (1)

Application Number Title Priority Date Filing Date
GB52279/69A Expired GB1256119A (en) 1968-11-21 1969-10-24 Turbine engine compressor

Country Status (5)

Country Link
BE (1) BE741845A (en)
CH (1) CH506714A (en)
DE (1) DE1958859A1 (en)
FR (1) FR2023770A1 (en)
GB (1) GB1256119A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2127905A (en) * 1982-09-30 1984-04-18 Gen Electric Centrifugal compressor
EP3018358A1 (en) * 2014-11-06 2016-05-11 General Electric Company Centrifugal compressor apparatus

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2127905A (en) * 1982-09-30 1984-04-18 Gen Electric Centrifugal compressor
US4502837A (en) * 1982-09-30 1985-03-05 General Electric Company Multi stage centrifugal impeller
EP3018358A1 (en) * 2014-11-06 2016-05-11 General Electric Company Centrifugal compressor apparatus
CN105673524A (en) * 2014-11-06 2016-06-15 通用电气公司 Centrifugal compressor apparatus
CN105673524B (en) * 2014-11-06 2019-01-22 通用电气公司 Centrifugal compressor apparatus
US10428823B2 (en) 2014-11-06 2019-10-01 General Electric Company Centrifugal compressor apparatus

Also Published As

Publication number Publication date
FR2023770A1 (en) 1970-08-21
DE1958859A1 (en) 1970-12-23
BE741845A (en) 1970-05-19
CH506714A (en) 1971-04-30

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