FR2323007A1 - Turbine blade cooling by fluid leakage through void by blade root - has void wall, with inclined coutlet bore, radial to blade platform - Google Patents

Turbine blade cooling by fluid leakage through void by blade root - has void wall, with inclined coutlet bore, radial to blade platform

Info

Publication number
FR2323007A1
FR2323007A1 FR7626901A FR7626901A FR2323007A1 FR 2323007 A1 FR2323007 A1 FR 2323007A1 FR 7626901 A FR7626901 A FR 7626901A FR 7626901 A FR7626901 A FR 7626901A FR 2323007 A1 FR2323007 A1 FR 2323007A1
Authority
FR
France
Prior art keywords
void
blade
bore
platform
wall
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.)
Withdrawn
Application number
FR7626901A
Other languages
French (fr)
Inventor
Melvin Bobo
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.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Publication of FR2323007A1 publication Critical patent/FR2323007A1/en
Withdrawn legal-status Critical Current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
    • F01D5/12—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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/80—Platforms for stationary or moving blades
    • F05D2240/81—Cooled platforms
    • 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

The fluid cooling arrangement is intended for a turbine blade comprising the blade profile itself (12), a platform (13) and a blade root (17) part of which is held in the rotor (10) whilst another portion partially bounds a void (44) which receive fluid leaking from a chamber upstream of the blades. A wall element (16) is provided, extending radially inwards from the platform and partially bounding the void. A bore (52) is provided in this wall, whose centre line is at an acute angle relative to the rotor axis, which bore serves as outlet for the fluid from the void. The bore centre line may be parallel to the downstream portion of the blade profile.
FR7626901A 1975-09-08 1976-09-07 Turbine blade cooling by fluid leakage through void by blade root - has void wall, with inclined coutlet bore, radial to blade platform Withdrawn FR2323007A1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US61113575A 1975-09-08 1975-09-08

Publications (1)

Publication Number Publication Date
FR2323007A1 true FR2323007A1 (en) 1977-04-01

Family

ID=24447777

Family Applications (1)

Application Number Title Priority Date Filing Date
FR7626901A Withdrawn FR2323007A1 (en) 1975-09-08 1976-09-07 Turbine blade cooling by fluid leakage through void by blade root - has void wall, with inclined coutlet bore, radial to blade platform

Country Status (4)

Country Link
JP (1) JPS5241717A (en)
DE (1) DE2639511A1 (en)
FR (1) FR2323007A1 (en)
IT (1) IT1063518B (en)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2439872A1 (en) * 1978-10-26 1980-05-23 Rolls Royce AIR-COOLED TURBINE FOR A GAS TURBINE ENGINE
FR2464363A1 (en) * 1979-08-30 1981-03-06 Rolls Royce TURBINE ROTOR FOR TURBOMACHINES WITH COOLANT TRANSFER SYSTEM
FR2468727A1 (en) * 1979-10-26 1981-05-08 Snecma IMPROVEMENT TO COOLED TURBINE AUBES
FR2485632A1 (en) * 1980-06-30 1981-12-31 Snecma IMPROVEMENT TO VENTILATION SYSTEMS OF TURBINE BLADES AND DISKS
FR2503246A1 (en) * 1981-04-01 1982-10-08 United Technologies Corp NOZZLE FOR COOLING ROTOR BLADE
FR2525279A1 (en) * 1982-04-19 1983-10-21 United Technologies Corp COOLING SYSTEM FOR TURBINES

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS55116592A (en) * 1979-03-01 1980-09-08 Yoshino Kogyosho Co Ltd Bottling method
JPS59163499U (en) * 1983-04-19 1984-11-01 日立造船株式会社 Workpiece delivery device
JPS6384018U (en) * 1986-11-20 1988-06-02
DE3736836A1 (en) * 1987-10-30 1989-05-11 Bbc Brown Boveri & Cie AXIAL FLOWED GAS TURBINE
JPH03115015A (en) * 1989-09-28 1991-05-16 Sekisui Chem Co Ltd Lengthy body sorter
DE19854907A1 (en) * 1998-11-27 2000-05-31 Rolls Royce Deutschland Cooling air conduction for high pressure axial aviation gas turbines with air flow guided through radial turbine, turbine plate, through ring gap, towards hub cob for cooling
DE19950109A1 (en) * 1999-10-18 2001-04-19 Asea Brown Boveri Rotor for a gas turbine
DE19957225A1 (en) * 1999-11-27 2001-06-07 Rolls Royce Deutschland Cooling-air conduction system, esp. for high-pressure turbine section of gas-turbine engine or power unit, has part of the air flowing past the gas-turbine combustion chamber conducted radially at the height of the second pre-spin chamber
EP2093381A1 (en) 2008-02-25 2009-08-26 Siemens Aktiengesellschaft Turbine blade or vane with cooled platform
EP2957722B1 (en) 2014-06-18 2019-04-10 United Technologies Corporation Rotor for a gas turbine engine

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2439872A1 (en) * 1978-10-26 1980-05-23 Rolls Royce AIR-COOLED TURBINE FOR A GAS TURBINE ENGINE
FR2464363A1 (en) * 1979-08-30 1981-03-06 Rolls Royce TURBINE ROTOR FOR TURBOMACHINES WITH COOLANT TRANSFER SYSTEM
FR2468727A1 (en) * 1979-10-26 1981-05-08 Snecma IMPROVEMENT TO COOLED TURBINE AUBES
US4456428A (en) * 1979-10-26 1984-06-26 S.N.E.C.M.A. Apparatus for cooling turbine blades
FR2485632A1 (en) * 1980-06-30 1981-12-31 Snecma IMPROVEMENT TO VENTILATION SYSTEMS OF TURBINE BLADES AND DISKS
EP0043300A2 (en) * 1980-06-30 1982-01-06 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Cooling system for turbine blades and discs
EP0043300A3 (en) * 1980-06-30 1982-01-13 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Cooling system for turbine blades and discs
FR2503246A1 (en) * 1981-04-01 1982-10-08 United Technologies Corp NOZZLE FOR COOLING ROTOR BLADE
FR2525279A1 (en) * 1982-04-19 1983-10-21 United Technologies Corp COOLING SYSTEM FOR TURBINES

Also Published As

Publication number Publication date
DE2639511A1 (en) 1977-03-17
IT1063518B (en) 1985-02-11
JPS5241717A (en) 1977-03-31

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Legal Events

Date Code Title Description
ST Notification of lapse