GB2021207A - Air-cooled Gas Turbines - Google Patents

Air-cooled Gas Turbines

Info

Publication number
GB2021207A
GB2021207A GB7915566A GB7915566A GB2021207A GB 2021207 A GB2021207 A GB 2021207A GB 7915566 A GB7915566 A GB 7915566A GB 7915566 A GB7915566 A GB 7915566A GB 2021207 A GB2021207 A GB 2021207A
Authority
GB
United Kingdom
Prior art keywords
air
flow
pressure
area
gas turbines
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.)
Granted
Application number
GB7915566A
Other versions
GB2021207B (en
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 GB7915566A priority Critical patent/GB2021207B/en
Publication of GB2021207A publication Critical patent/GB2021207A/en
Application granted granted Critical
Publication of GB2021207B publication Critical patent/GB2021207B/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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
    • F01D11/04—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type using sealing fluid, e.g. steam
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
    • 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)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

A source of cooling air at a high supply pressure is fed through first and second passages (21, 32) to first and second area (24, 25) of a turbine rotor, the areas being separated by a seal (34). The pressure in the first area (24) is less than the supply pressure and the pressure in the second area (35), is less than the pressure in the first area. In order to reduce the leakage flow in the seal (34) the seal is arranged to incorporate part of the second passage (32) in which at least part of the second flow of air is directed to flow against the flow of leakage air so as to reduce the leakage flow and simultaneously to reduce the pressure of the second flow of air. <IMAGE>
GB7915566A 1978-05-20 1979-05-04 Aircooled gas turbines Expired GB2021207B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB7915566A GB2021207B (en) 1978-05-20 1979-05-04 Aircooled gas turbines

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB2095178 1978-05-20
GB7915566A GB2021207B (en) 1978-05-20 1979-05-04 Aircooled gas turbines

Publications (2)

Publication Number Publication Date
GB2021207A true GB2021207A (en) 1979-11-28
GB2021207B GB2021207B (en) 1982-04-28

Family

ID=26255004

Family Applications (1)

Application Number Title Priority Date Filing Date
GB7915566A Expired GB2021207B (en) 1978-05-20 1979-05-04 Aircooled gas turbines

Country Status (1)

Country Link
GB (1) GB2021207B (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2253442A (en) * 1991-03-02 1992-09-09 Rolls Royce Plc Multi-stage seal for an axial flow turbine
GB2452297A (en) * 2007-08-30 2009-03-04 Rolls Royce Plc Compressor leakage flow control

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2253442A (en) * 1991-03-02 1992-09-09 Rolls Royce Plc Multi-stage seal for an axial flow turbine
US5205706A (en) * 1991-03-02 1993-04-27 Rolls-Royce Plc Axial flow turbine assembly and a multi-stage seal
GB2253442B (en) * 1991-03-02 1994-08-24 Rolls Royce Plc An axial flow turbine assembly
GB2452297A (en) * 2007-08-30 2009-03-04 Rolls Royce Plc Compressor leakage flow control
GB2452297B (en) * 2007-08-30 2010-01-06 Rolls Royce Plc A compressor

Also Published As

Publication number Publication date
GB2021207B (en) 1982-04-28

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Legal Events

Date Code Title Description
PCNP Patent ceased through non-payment of renewal fee