GB2010404A - Cooling Turbine Rotor Blades - Google Patents

Cooling Turbine Rotor Blades

Info

Publication number
GB2010404A
GB2010404A GB7846540A GB7846540A GB2010404A GB 2010404 A GB2010404 A GB 2010404A GB 7846540 A GB7846540 A GB 7846540A GB 7846540 A GB7846540 A GB 7846540A GB 2010404 A GB2010404 A GB 2010404A
Authority
GB
United Kingdom
Prior art keywords
cooling air
channel
flange
disc
turbine rotor
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
GB7846540A
Other versions
GB2010404B (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 GB7846540A priority Critical patent/GB2010404B/en
Priority to IT30937/78A priority patent/IT1160359B/en
Publication of GB2010404A publication Critical patent/GB2010404A/en
Application granted granted Critical
Publication of GB2010404B publication Critical patent/GB2010404B/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
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
    • F01D5/082—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades on the side of the rotor disc
    • 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
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection cooling
    • 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • F01D5/3015—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type with side plates

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

A turbine rotor disc has a rim in which are formed generally axially extending slots receiving the roots (24) of blades (20). A cooling air passage (28) is defined between the bottom of each slot and its respective blade root. An annular flange (38) extends axially from a side face of the disc and provides a continuous surface at a radius just less than that of the slots. An annular cooling air channel (40) is formed between the side face of the disc and the radially inner part of the flange (38), the channel being open to the radially inner side of the flange and being of sufficient radial depth to intersect the bottom surfaces and part of the flanks of each of the slots so that cooling air supplied through nozzles 50 can flow from the channel to passages 28 and thence to passages 46, 48 with the blades. <IMAGE>
GB7846540A 1977-12-17 1978-11-29 Gas turbine engines Expired GB2010404B (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
GB7846540A GB2010404B (en) 1977-12-17 1978-11-29 Gas turbine engines
IT30937/78A IT1160359B (en) 1977-12-17 1978-12-15 REFINEMENTS MADE TO GAS TURBINE ENGINES

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB5259777 1977-12-17
GB7846540A GB2010404B (en) 1977-12-17 1978-11-29 Gas turbine engines

Publications (2)

Publication Number Publication Date
GB2010404A true GB2010404A (en) 1979-06-27
GB2010404B GB2010404B (en) 1982-02-10

Family

ID=26267099

Family Applications (1)

Application Number Title Priority Date Filing Date
GB7846540A Expired GB2010404B (en) 1977-12-17 1978-11-29 Gas turbine engines

Country Status (2)

Country Link
GB (1) GB2010404B (en)
IT (1) IT1160359B (en)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2464363A1 (en) * 1979-08-30 1981-03-06 Rolls Royce TURBINE ROTOR FOR TURBOMACHINES WITH COOLANT TRANSFER SYSTEM
US4730983A (en) * 1986-09-03 1988-03-15 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" System for attaching a rotor blade to a rotor disk
US4807433A (en) * 1983-05-05 1989-02-28 General Electric Company Turbine cooling air modulation
GB2225063A (en) * 1988-10-21 1990-05-23 Mtu Muenchen Gmbh Turbine cooling arrangement
US6561764B1 (en) * 1999-03-19 2003-05-13 Siemens Aktiengesellschaft Gas turbine rotor with an internally cooled gas turbine blade and connecting configuration including an insert strip bridging adjacent blade platforms
US6884023B2 (en) * 2002-09-27 2005-04-26 United Technologies Corporation Integral swirl knife edge injection assembly
EP2092996A1 (en) 2008-02-14 2009-08-26 United Technologies Corporation Method and apparatus for as-cast seal on turbine blades
EP2843196A1 (en) * 2013-09-03 2015-03-04 Techspace Aero S.A. Compressor of an axial turbomachine with brush seal and corresponding turbomachine

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2464363A1 (en) * 1979-08-30 1981-03-06 Rolls Royce TURBINE ROTOR FOR TURBOMACHINES WITH COOLANT TRANSFER SYSTEM
US4807433A (en) * 1983-05-05 1989-02-28 General Electric Company Turbine cooling air modulation
US4730983A (en) * 1986-09-03 1988-03-15 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" System for attaching a rotor blade to a rotor disk
GB2225063A (en) * 1988-10-21 1990-05-23 Mtu Muenchen Gmbh Turbine cooling arrangement
GB2225063B (en) * 1988-10-21 1992-12-02 Mtu Muenchen Gmbh Gas turbine having cooling means
US6561764B1 (en) * 1999-03-19 2003-05-13 Siemens Aktiengesellschaft Gas turbine rotor with an internally cooled gas turbine blade and connecting configuration including an insert strip bridging adjacent blade platforms
US6884023B2 (en) * 2002-09-27 2005-04-26 United Technologies Corporation Integral swirl knife edge injection assembly
EP2092996A1 (en) 2008-02-14 2009-08-26 United Technologies Corporation Method and apparatus for as-cast seal on turbine blades
US7918265B2 (en) 2008-02-14 2011-04-05 United Technologies Corporation Method and apparatus for as-cast seal on turbine blades
EP2843196A1 (en) * 2013-09-03 2015-03-04 Techspace Aero S.A. Compressor of an axial turbomachine with brush seal and corresponding turbomachine
RU2615300C2 (en) * 2013-09-03 2017-04-04 Сафран Аэро Бустерс Са Compressor of axial turbine machine and axial turbine machine

Also Published As

Publication number Publication date
IT7830937A0 (en) 1978-12-15
GB2010404B (en) 1982-02-10
IT1160359B (en) 1987-03-11

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Legal Events

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

Effective date: 19941129