GB1096257A - Gas turbine engine - Google Patents

Gas turbine engine

Info

Publication number
GB1096257A
GB1096257A GB26021/66A GB2602166A GB1096257A GB 1096257 A GB1096257 A GB 1096257A GB 26021/66 A GB26021/66 A GB 26021/66A GB 2602166 A GB2602166 A GB 2602166A GB 1096257 A GB1096257 A GB 1096257A
Authority
GB
United Kingdom
Prior art keywords
recesses
casing
gas turbine
turbine engine
blades
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
GB26021/66A
Inventor
Richard Derby Beale
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.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
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
Priority to GB1609061A priority Critical patent/GB949231A/en
Priority to FR895507A priority patent/FR1339521A/en
Priority to DER32617A priority patent/DE1278178B/en
Application filed by Rolls Royce PLC filed Critical Rolls Royce PLC
Priority to GB26021/66A priority patent/GB1096257A/en
Publication of GB1096257A publication Critical patent/GB1096257A/en
Expired legal-status Critical Current

Links

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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
    • 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
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • 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
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

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

Abstract

1,096,257. Compressor blade fixing. ROLLS-ROYCE Ltd. June 10, 1966, No.26021/66. Addition to 949, 231. Heading F1T. In a modification of the invention of Specification 949, 231, the radially inner ends of synthetic resin compressor inlet guide blades 17 are heat bonded in registering recesses 20 in the axially extending abutting flanges 23 of two spaced annular channel-section resin members 21. The outer ends of the blades are mounted in recesses in an inner casing 22 surrounded by the engine casing 11. Casing 22 may also be provided with registering recesses similar to recesses 20.
GB26021/66A 1961-05-03 1966-06-10 Gas turbine engine Expired GB1096257A (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
GB1609061A GB949231A (en) 1961-05-03 1961-05-03 Gas turbine engine
FR895507A FR1339521A (en) 1966-06-10 1962-04-25 Fluid circulation machine
DER32617A DE1278178B (en) 1966-06-10 1962-05-03 Inlet guide vane ring for axial compressors of gas turbine engines
GB26021/66A GB1096257A (en) 1966-06-10 1966-06-10 Gas turbine engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB26021/66A GB1096257A (en) 1966-06-10 1966-06-10 Gas turbine engine

Publications (1)

Publication Number Publication Date
GB1096257A true GB1096257A (en) 1967-12-20

Family

ID=10237120

Family Applications (1)

Application Number Title Priority Date Filing Date
GB26021/66A Expired GB1096257A (en) 1961-05-03 1966-06-10 Gas turbine engine

Country Status (3)

Country Link
DE (1) DE1278178B (en)
FR (1) FR1339521A (en)
GB (1) GB1096257A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0399879A1 (en) * 1989-05-23 1990-11-28 Societe Europeenne De Propulsion Stator assembly for turbojet and its method of manufacture

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE966949C (en) * 1943-01-16 1957-09-19 Karl Wernert Housing made of plastic to be cast or pressed for centrifugal pumps, blowers or the like.
BE487115A (en) * 1946-04-05
US2609176A (en) * 1950-01-21 1952-09-02 A V Roe Canada Ltd Turbine nozzle guide vane construction
GB695724A (en) * 1950-08-01 1953-08-19 Rolls Royce Improvements in or relating to structural elements for axial-flow turbo-machines such as compressors or turbines of gas-turbine engines
US2749026A (en) * 1951-02-27 1956-06-05 United Aircraft Corp Stator construction for compressors
US2801075A (en) * 1952-12-22 1957-07-30 Gen Motors Corp Turbine nozzle
US2834537A (en) * 1954-01-18 1958-05-13 Ryan Aeronautical Co Compressor stator structure
US2868439A (en) * 1954-05-07 1959-01-13 Goodyear Aircraft Corp Plastic axial-flow compressor for gas turbines
DE1067971B (en) * 1955-10-18 1959-10-29
US2951631A (en) * 1956-01-25 1960-09-06 Fairchild Engine & Airplane Engine accessory drive
GB805545A (en) * 1956-02-06 1958-12-10 Rolls Royce Improvements in or relating to axial-flow fluid machines for example axial-flow turbines of gas-turbine engines
BE570267A (en) * 1957-08-16

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0399879A1 (en) * 1989-05-23 1990-11-28 Societe Europeenne De Propulsion Stator assembly for turbojet and its method of manufacture
FR2647502A1 (en) * 1989-05-23 1990-11-30 Europ Propulsion TURBINE DISTRIBUTOR FOR TURBO-REACTOR AND MANUFACTURING METHOD THEREOF
US5074749A (en) * 1989-05-23 1991-12-24 Societe Europeenne De Propulsion Turbine stator for a turbojet, and method of manufacture

Also Published As

Publication number Publication date
FR1339521A (en) 1963-10-11
DE1278178B (en) 1968-09-19

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