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GB710862A - Improvements in or relating to gas-turbine plant - Google Patents

Improvements in or relating to gas-turbine plant

Info

Publication number
GB710862A
GB710862A GB3257/51A GB325751A GB710862A GB 710862 A GB710862 A GB 710862A GB 3257/51 A GB3257/51 A GB 3257/51A GB 325751 A GB325751 A GB 325751A GB 710862 A GB710862 A GB 710862A
Authority
GB
United Kingdom
Prior art keywords
turbine
interconnected
compressor
struts
shaft
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
GB3257/51A
Inventor
Terence Edward Gouven Gardiner
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
Application filed by Rolls Royce PLC filed Critical Rolls Royce PLC
Priority to GB3257/51A priority Critical patent/GB710862A/en
Publication of GB710862A publication Critical patent/GB710862A/en
Expired legal-status Critical Current

Links

Classifications

    • 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
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/20—Mounting or supporting of plant; Accommodating heat expansion or creep
    • 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)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

710,862. Gas turbine plant; centrifugal compressors. ROLLS-ROYCE, Ltd. May 8, 1952 [Feb. 9, 1951], No. 3257/51. Classes 110(1) and 110(3) In a' gas turbine plant comprising combustion equipment 14, Fig. 2, disposed axially between an axial-flow turbine 11 and a compressor 10 and wherein the turbine and compressor rotors are interconnected by a shaft 12 extending centrally of the combustion equipment, the compressor and turbine stationary structures are interconnected by an intermediate structure which is located radially between the shaft and the combustion equipment and comprises one or more sets of tubular struts or stays arranged in a zig-zag pattern. As shown in Fig. 1 the structure comprises struts 35-39 interconnected by rings 30, 31. 32, 41 and is made of aluminium. Extensions 39a are slidably spigoted in sockets 40 formed in the turbine stator structure 11b and supports the bearings 28,.29. The front bearing of the rotor assembly is supported by a tubular aluminium structure 23, 25. 26. 27 which is welded to the bearing housing 24 and to an annular structure 17. The engine accessory drive casing 51 is supported from the rings 23, 25 by struts 52. The compressor stator comprises inlet sections 10b with cascades 10c secured therein by stays 16, the sections 10b being interconnected by the members 17 which are bolted together. The diffuser vane assembly 15 is die cast in segments which are radially located in the members 17. The shaft 12 is formed in two parts interconnected by a universal coupling 13 and is protected by an aluminium sheet metal fairing 42 and a sheet metal member 43. Air is tapped off from the compressor at 44 and fed to the bearings and labyrinth packings through tubes 46 and the struts. The turbine rotor or a separate turbine rotor may drive an airscrew or the plant may constitute a turbo-jet unit.
GB3257/51A 1951-02-09 1951-02-09 Improvements in or relating to gas-turbine plant Expired GB710862A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB3257/51A GB710862A (en) 1951-02-09 1951-02-09 Improvements in or relating to gas-turbine plant

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB3257/51A GB710862A (en) 1951-02-09 1951-02-09 Improvements in or relating to gas-turbine plant

Publications (1)

Publication Number Publication Date
GB710862A true GB710862A (en) 1954-06-23

Family

ID=9754918

Family Applications (1)

Application Number Title Priority Date Filing Date
GB3257/51A Expired GB710862A (en) 1951-02-09 1951-02-09 Improvements in or relating to gas-turbine plant

Country Status (1)

Country Link
GB (1) GB710862A (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0161562A3 (en) * 1984-05-15 1987-05-20 A. S. Kongsberg Väpenfabrikk Apparatus for mounting, and for maintaining running clearance in, a double entry radial compressor
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
WO1992018760A1 (en) * 1991-04-17 1992-10-29 Rolls-Royce Plc A combustion chamber assembly
WO2009142552A1 (en) * 2008-05-20 2009-11-26 Volvo Aero Corporation A gas turbine engine, a structural unit for a gas turbine engine and a method for manufacturing a structural unit

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0161562A3 (en) * 1984-05-15 1987-05-20 A. S. Kongsberg Väpenfabrikk Apparatus for mounting, and for maintaining running clearance in, a double entry radial compressor
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
WO1992018760A1 (en) * 1991-04-17 1992-10-29 Rolls-Royce Plc A combustion chamber assembly
US5353586A (en) * 1991-04-17 1994-10-11 Rolls-Royce Plc Combustion chamber assembly with hollow support strut for carrying cooling air
JP3142563B2 (en) 1991-04-17 2001-03-07 ロールス・ロイス・ピーエルシー Combustion chamber assembly
WO2009142552A1 (en) * 2008-05-20 2009-11-26 Volvo Aero Corporation A gas turbine engine, a structural unit for a gas turbine engine and a method for manufacturing a structural unit

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