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GB1541533A - Gas turbine assemblies - Google Patents

Gas turbine assemblies

Info

Publication number
GB1541533A
GB1541533A GB30984/77A GB3098477A GB1541533A GB 1541533 A GB1541533 A GB 1541533A GB 30984/77 A GB30984/77 A GB 30984/77A GB 3098477 A GB3098477 A GB 3098477A GB 1541533 A GB1541533 A GB 1541533A
Authority
GB
United Kingdom
Prior art keywords
compressor
cooling air
gas turbine
rotor
intermediate stage
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
GB30984/77A
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.)
Kraftwerk Union AG
Original Assignee
Kraftwerk Union AG
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 Kraftwerk Union AG filed Critical Kraftwerk Union AG
Publication of GB1541533A publication Critical patent/GB1541533A/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
    • 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
    • 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
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors

Landscapes

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

Abstract

The gas turbine installation is supplied with cooling air (7) which is removed from an intermediate stage (4) of the compressor (2) and is passed to the turbine (3) within the rotor (1). The removal of the cooling air (7) from the intermediate stage (4) of the compressor (2) takes place via a guiding means (8) such that, when it emerges from the guide means (8), it flows approximately tangentially and has a velocity relative to the rotating system which is approximately equal to the peripheral velocity of the boundary walls but is directed in the opposite direction to the latter. The cooling air (7) can thereby be introduced into the rotor (1) with a low absolute velocity and, as a result, the pressure losses are small. In this gas turbine installation, cooling air (7) can be removed from a low-order intermediate stage (4) of the compressor (2) with a low outlay on construction and with a minimum pressure loss, having a correspondingly low temperature, and fed to the turbine blades to be cooled close to the axis of the rotor (1). In addition to an improved cooling efficiency, this reduces the power consumption of the compressor (2) and correspondingly increases the effective output of the gas turbine installation. <IMAGE>
GB30984/77A 1976-07-23 1977-07-22 Gas turbine assemblies Expired GB1541533A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE19762633222 DE2633222A1 (en) 1976-07-23 1976-07-23 GAS TURBINE SYSTEM WITH COOLING OF TURBINE PARTS

Publications (1)

Publication Number Publication Date
GB1541533A true GB1541533A (en) 1979-03-07

Family

ID=5983795

Family Applications (1)

Application Number Title Priority Date Filing Date
GB30984/77A Expired GB1541533A (en) 1976-07-23 1977-07-22 Gas turbine assemblies

Country Status (5)

Country Link
CH (1) CH621387A5 (en)
DE (1) DE2633222A1 (en)
GB (1) GB1541533A (en)
IT (1) IT1085836B (en)
SE (1) SE420635B (en)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3037020A1 (en) * 1980-10-01 1982-05-13 MTU Motoren- und Turbinen-Union München GmbH, 8000 München DEVICE FOR COOLING AIR DIRECTION AT GAS TURBINE ENGINES
GB2118629A (en) * 1982-04-21 1983-11-02 Rolls Royce Device for passing a fluid flow eg. cooling air through a barrier eg. bolted joint
GB2420155A (en) * 2004-11-12 2006-05-17 Rolls Royce Plc Cooling air is diffused and then re-pressurised by radial compressor attached to turbine disc
US7159402B2 (en) 2001-12-05 2007-01-09 Rolls-Royce Deutschland Ltd & Co Kg Vortex reducer in the high-pressure compressor of a gas turbine
JP2013204593A (en) * 2012-03-29 2013-10-07 General Electric Co <Ge> Apparatus and method for purging gas turbine rotor
US9382802B2 (en) 2011-07-26 2016-07-05 General Electric Technology Gmbh Compressor rotor

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4008977A (en) * 1975-09-19 1977-02-22 United Technologies Corporation Compressor bleed system
GB2075123B (en) * 1980-05-01 1983-11-16 Gen Electric Turbine cooling air deswirler
FR2491549B1 (en) * 1980-10-08 1985-07-05 Snecma DEVICE FOR COOLING A GAS TURBINE, BY TAKING AIR FROM THE COMPRESSOR
US4674955A (en) * 1984-12-21 1987-06-23 The Garrett Corporation Radial inboard preswirl system
DE4324034A1 (en) * 1993-07-17 1995-01-19 Abb Management Ag Gas turbine with a cooled rotor
DE19852604A1 (en) 1998-11-14 2000-05-18 Abb Research Ltd Rotor for gas turbine, with first cooling air diverting device having several radial borings running inwards through first rotor disk
CH705840A1 (en) 2011-12-06 2013-06-14 Alstom Technology Ltd High-pressure compressor, in particular in a gas turbine.
EP3056666A1 (en) * 2015-02-13 2016-08-17 Siemens Aktiengesellschaft Wheel disc element for two blade rows, compressor impeller, turbo engine and method for regulating the temperature of such a double wheel disc element

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3037020A1 (en) * 1980-10-01 1982-05-13 MTU Motoren- und Turbinen-Union München GmbH, 8000 München DEVICE FOR COOLING AIR DIRECTION AT GAS TURBINE ENGINES
GB2118629A (en) * 1982-04-21 1983-11-02 Rolls Royce Device for passing a fluid flow eg. cooling air through a barrier eg. bolted joint
US4551062A (en) * 1982-04-21 1985-11-05 Rolls-Royce Limited Device for passing a fluid flow through a barrier
US7159402B2 (en) 2001-12-05 2007-01-09 Rolls-Royce Deutschland Ltd & Co Kg Vortex reducer in the high-pressure compressor of a gas turbine
GB2420155A (en) * 2004-11-12 2006-05-17 Rolls Royce Plc Cooling air is diffused and then re-pressurised by radial compressor attached to turbine disc
GB2420155B (en) * 2004-11-12 2008-08-27 Rolls Royce Plc Turbine blade cooling system
US7458766B2 (en) 2004-11-12 2008-12-02 Rolls-Royce Plc Turbine blade cooling system
US9382802B2 (en) 2011-07-26 2016-07-05 General Electric Technology Gmbh Compressor rotor
JP2013204593A (en) * 2012-03-29 2013-10-07 General Electric Co <Ge> Apparatus and method for purging gas turbine rotor

Also Published As

Publication number Publication date
IT1085836B (en) 1985-05-28
SE420635B (en) 1981-10-19
CH621387A5 (en) 1981-01-30
DE2633222A1 (en) 1978-01-26
SE7707890L (en) 1978-01-24

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Legal Events

Date Code Title Description
PS Patent sealed [section 19, patents act 1949]
PCNP Patent ceased through non-payment of renewal fee