GB1359983A - Creation of Inventions and Patents with Artificial Intelligence

GB1359983A – Cooled guide blades for gas turbines
– Google Patents

GB1359983A – Cooled guide blades for gas turbines
– Google Patents
Cooled guide blades for gas turbines

Info

Publication number
GB1359983A

GB1359983A
GB247973A
GB247973A
GB1359983A
GB 1359983 A
GB1359983 A
GB 1359983A
GB 247973 A
GB247973 A
GB 247973A
GB 247973 A
GB247973 A
GB 247973A
GB 1359983 A
GB1359983 A
GB 1359983A
Authority
GB
United Kingdom
Prior art keywords
chamber
duct
exit
trailing edge
blade
Prior art date
1972-01-18
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
GB247973A
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.)

Brown Boveri Sulzer Turbomaschinen AG

Original Assignee
Brown Boveri Sulzer Turbomaschinen 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.)
1972-01-18
Filing date
1973-01-17
Publication date
1974-07-17

1973-01-17
Application filed by Brown Boveri Sulzer Turbomaschinen AG
filed
Critical
Brown Boveri Sulzer Turbomaschinen AG

1974-07-17
Publication of GB1359983A
publication
Critical
patent/GB1359983A/en

Status
Expired
legal-status
Critical
Current

Links

Espacenet

Global Dossier

Discuss

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

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

F01D9/00—Stators

F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles

F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector

F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using 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

F05D2260/00—Function

F05D2260/20—Heat transfer, e.g. cooling

F05D2260/221—Improvement of heat transfer

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

F05D2260/00—Function

F05D2260/20—Heat transfer, e.g. cooling

F05D2260/221—Improvement of heat transfer

F05D2260/2214—Improvement of heat transfer by increasing the heat transfer surface

F05D2260/22141—Improvement of heat transfer by increasing the heat transfer surface using fins or ribs

Abstract

1359983 Turbine blades BROWN BOVERISULZER TURBOMACHINERY Ltd 17 Jan 1973 [18 Jan 1972] 2479/73 Heading FIT A gas turbine guide blade is provided with two cooling air-flow paths, a first path extending from a chamber 13 within platform 14, along leading edge duct 15 to second chamber 16 within platform 17 at the other end of the blade, chamber 16 communicating with an exit 18 adjacent trailing edge 19, and a second path extending from chamber 13 to a second exit 24 also adjacent trailing edge 19. The second path comprises a duct 20 of greater cross-section than duct 15 and connecting via chamber 21 with a duct 22 having fins 25, duct 22 connecting via chamber 23 with exit 24. A transverse partition 26 separates exits 18, 24, the latter including fins 30. Exits 18, 24 may discharge immediately at trailing edge 19 or to one or other side thereof Figs. 2 to 4 (not shown). The blade is formed by casting, plates 27, 28, 29 being subsequently welded in position.

GB247973A
1972-01-18
1973-01-17
Cooled guide blades for gas turbines

Expired

GB1359983A
(en)

Applications Claiming Priority (1)

Application Number
Priority Date
Filing Date
Title

CH69972

1972-01-18

Publications (1)

Publication Number
Publication Date

GB1359983A
true

GB1359983A
(en)

1974-07-17

Family
ID=4193097
Family Applications (1)

Application Number
Title
Priority Date
Filing Date

GB247973A
Expired

GB1359983A
(en)

1972-01-18
1973-01-17
Cooled guide blades for gas turbines

Country Status (11)

Country
Link

US
(1)

US3807892A
(en)

JP
(1)

JPS5145726B2
(en)

BE
(1)

BE794195A
(en)

CA
(1)

CA967095A
(en)

CH
(1)

CH547431A
(en)

DE
(1)

DE2202858C2
(en)

FR
(1)

FR2168802A5
(en)

GB
(1)

GB1359983A
(en)

IT
(1)

IT978243B
(en)

NL
(1)

NL164358C
(en)

SE
(1)

SE381311B
(en)

Cited By (2)

* Cited by examiner, † Cited by third party

Publication number
Priority date
Publication date
Assignee
Title

GB2345942A
(en)

1998-12-24
2000-07-26
Rolls Royce Plc
Gas turbine engine blade cooling air system

GB2366600A
(en)

2000-09-09
2002-03-13
Rolls Royce Plc
Cooling arrangement for trailing edge of aerofoil

Families Citing this family (69)

* Cited by examiner, † Cited by third party

Publication number
Priority date
Publication date
Assignee
Title

CH580750A5
(en)

1974-07-17
1976-10-15
Bbc Sulzer Turbomaschinen

CH582305A5
(en)

1974-09-05
1976-11-30
Bbc Sulzer Turbomaschinen

US4025226A
(en)

1975-10-03
1977-05-24
United Technologies Corporation
Air cooled turbine vane

US4236870A
(en)

1977-12-27
1980-12-02
United Technologies Corporation
Turbine blade

US4278400A
(en)

1978-09-05
1981-07-14
United Technologies Corporation
Coolable rotor blade

JPS5540221A
(en)

1978-09-14
1980-03-21
Hitachi Ltd
Cooling structure of gas turbin blade

US4303374A
(en)

1978-12-15
1981-12-01
General Electric Company
Film cooled airfoil body

JPS6056883B2
(en)

1979-02-28
1985-12-12
株式会社東芝

gas turbine moving blades

GB2100807B
(en)

1981-06-30
1984-08-01
Rolls Royce
Turbine blade for gas turbine engines

GB2163218B
(en)

1981-07-07
1986-07-16
Rolls Royce
Cooled vane or blade for a gas turbine engine

US4474532A
(en)

1981-12-28
1984-10-02
United Technologies Corporation
Coolable airfoil for a rotary machine

US4767268A
(en)

1987-08-06
1988-08-30
United Technologies Corporation
Triple pass cooled airfoil

US4753575A
(en)

1987-08-06
1988-06-28
United Technologies Corporation
Airfoil with nested cooling channels

US5030060A
(en)

1988-10-20
1991-07-09
The United States Of America As Represented By The Secretary Of The Air Force
Method and apparatus for cooling high temperature ceramic turbine blade portions

FR2678318B1
(en)

1991-06-25
1993-09-10
Snecma

COOLED VANE OF TURBINE DISTRIBUTOR.

FR2681095B1
(en)

1991-09-05
1993-11-19
Snecma

CARENE TURBINE DISTRIBUTOR.

US5591002A
(en)

1994-08-23
1997-01-07
General Electric Co.
Closed or open air cooling circuits for nozzle segments with wheelspace purge

US5634766A
(en)

1994-08-23
1997-06-03
General Electric Co.
Turbine stator vane segments having combined air and steam cooling circuits

US5503529A
(en)

1994-12-08
1996-04-02
General Electric Company
Turbine blade having angled ejection slot

US5536143A
(en)

1995-03-31
1996-07-16
General Electric Co.
Closed circuit steam cooled bucket

US5741117A
(en)

1996-10-22
1998-04-21
United Technologies Corporation
Method for cooling a gas turbine stator vane

JP3426902B2
(en)

1997-03-11
2003-07-14
三菱重工業株式会社

Gas turbine cooling vane

US5902093A
(en)

1997-08-22
1999-05-11
General Electric Company
Crack arresting rotor blade

EP1073827B1
(en)

1998-04-21
2003-10-08
Siemens Aktiengesellschaft
Turbine blade

EP1099825A1
(en)

1999-11-12
2001-05-16
Siemens Aktiengesellschaft
Turbine blade and production method therefor

US6343911B1
(en)

2000-04-05
2002-02-05
General Electric Company
Side wall cooling for nozzle segments for a gas turbine

US6419445B1
(en)

2000-04-11
2002-07-16
General Electric Company
Apparatus for impingement cooling a side wall adjacent an undercut region of a turbine nozzle segment

US6453557B1
(en)

2000-04-11
2002-09-24
General Electric Company
Method of joining a vane cavity insert to a nozzle segment of a gas turbine

US6386825B1
(en)

2000-04-11
2002-05-14
General Electric Company
Apparatus and methods for impingement cooling of a side wall of a turbine nozzle segment

US6375415B1
(en)

2000-04-25
2002-04-23
General Electric Company
Hook support for a closed circuit fluid cooled gas turbine nozzle stage segment

US6439837B1
(en)

2000-06-27
2002-08-27
General Electric Company
Nozzle braze backside cooling

US6454526B1
(en)

2000-09-28
2002-09-24
Siemens Westinghouse Power Corporation
Cooled turbine vane with endcaps

US6508620B2
(en)

2001-05-17
2003-01-21
Pratt & Whitney Canada Corp.
Inner platform impingement cooling by supply air from outside

US6527514B2
(en)

2001-06-11
2003-03-04
Alstom (Switzerland) Ltd
Turbine blade with rub tolerant cooling construction

US6634858B2
(en)

2001-06-11
2003-10-21
Alstom (Switzerland) Ltd
Gas turbine airfoil

FR2833298B1
(en)

2001-12-10
2004-08-06
Snecma Moteurs

IMPROVEMENTS TO THE THERMAL BEHAVIOR OF THE TRAILING EDGE OF A HIGH-PRESSURE TURBINE BLADE

CH695702A5
(en)

2002-01-15
2006-07-31
Alstom Technology Ltd
Turbine vane, for a gas turbine, has inner cooling channels in a serpentine structure, with flow connections through hairpin bends

ATE291677T1
(en)

2002-01-17
2005-04-15
Siemens Ag

TURBINE BLADE WITH A HOT GAS PLATFORM AND A LOAD PLATFORM

US6860108B2
(en)

2003-01-22
2005-03-01
Mitsubishi Heavy Industries, Ltd.
Gas turbine tail tube seal and gas turbine using the same

US6969233B2
(en)

2003-02-27
2005-11-29
General Electric Company
Gas turbine engine turbine nozzle segment with a single hollow vane having a bifurcated cavity

US6984101B2
(en)

2003-07-14
2006-01-10
Siemens Westinghouse Power Corporation
Turbine vane plate assembly

US6929445B2
(en)

2003-10-22
2005-08-16
General Electric Company
Split flow turbine nozzle

US7029228B2
(en)

2003-12-04
2006-04-18
General Electric Company
Method and apparatus for convective cooling of side-walls of turbine nozzle segments

EP1571295A1
(en)

2004-03-01
2005-09-07
ALSTOM Technology Ltd
Cooled blade of a turbomachine and method of cooling

US7210906B2
(en)

2004-08-10
2007-05-01
Pratt & Whitney Canada Corp.
Internally cooled gas turbine airfoil and method

US7238003B2
(en)

2004-08-24
2007-07-03
Pratt & Whitney Canada Corp.
Vane attachment arrangement

US7189060B2
(en)

2005-01-07
2007-03-13
Siemens Power Generation, Inc.
Cooling system including mini channels within a turbine blade of a turbine engine

RU2425982C2
(en)

2005-04-14
2011-08-10
Альстом Текнолоджи Лтд
Gas turbine vane

US20090003987A1
(en)

2006-12-21
2009-01-01
Jack Raul Zausner
Airfoil with improved cooling slot arrangement

GB0813839D0
(en)

2008-07-30
2008-09-03
Rolls Royce Plc
An aerofoil and method for making an aerofoil

ES2389034T3
(en)

2009-05-19
2012-10-22
Alstom Technology Ltd

Gas turbine blade with improved cooling

US8500392B2
(en)

2009-10-01
2013-08-06
Pratt & Whitney Canada Corp.
Sealing for vane segments

US8616834B2
(en)

2010-04-30
2013-12-31
General Electric Company
Gas turbine engine airfoil integrated heat exchanger

US8777568B2
(en)

2010-09-30
2014-07-15
General Electric Company
Apparatus and methods for cooling platform regions of turbine rotor blades

US8840369B2
(en)

2010-09-30
2014-09-23
General Electric Company
Apparatus and methods for cooling platform regions of turbine rotor blades

US9145780B2
(en)

2011-12-15
2015-09-29
United Technologies Corporation
Gas turbine engine airfoil cooling circuit

US9151164B2
(en)

2012-03-21
2015-10-06
Pratt & Whitney Canada Corp.
Dual-use of cooling air for turbine vane and method

WO2014009074A1
(en)

2012-07-12
2014-01-16
Siemens Aktiengesellschaft
Turbine blade for a gas turbine

US9359902B2
(en)

2013-06-28
2016-06-07
Siemens Energy, Inc.
Turbine airfoil with ambient cooling system

RU2568763C2
(en)

2014-01-30
2015-11-20
Альстом Текнолоджи Лтд
Gas turbine component

US9771816B2
(en)

2014-05-07
2017-09-26
General Electric Company
Blade cooling circuit feed duct, exhaust duct, and related cooling structure

US20170234142A1
(en)

2016-02-17
2017-08-17
General Electric Company
Rotor Blade Trailing Edge Cooling

US10156146B2
(en)

2016-04-25
2018-12-18
General Electric Company
Airfoil with variable slot decoupling

KR101882104B1
(en)

2016-12-20
2018-07-25
두산중공업 주식회사
Gas turbine

US20200024967A1
(en)

2018-07-20
2020-01-23
United Technologies Corporation
Airfoil having angled trailing edge slots

US11028700B2
(en)

2018-11-09
2021-06-08
Raytheon Technologies Corporation
Airfoil with cooling passage circuit through platforms and airfoil section

EP3862537A1
(en)

2020-02-10
2021-08-11
General Electric Company Polska sp. z o.o.
Cooled turbine nozzle and nozzle segment

GB202117857D0
(en)

2021-12-10
2022-01-26
Rolls Royce Plc
Vane assembly for a gas turbine engine

CN115075891A
(en)

2022-05-29
2022-09-20
中国船舶重工集团公司第七0三研究所
Air-cooled turbine guide vane trailing edge structure with pressure side exhaust

Family Cites Families (3)

* Cited by examiner, † Cited by third party

Publication number
Priority date
Publication date
Assignee
Title

US3017159A
(en)

1956-11-23
1962-01-16
Curtiss Wright Corp
Hollow blade construction

US3533711A
(en)

1966-02-26
1970-10-13
Gen Electric
Cooled vane structure for high temperature turbines

US3623825A
(en)

1969-11-13
1971-11-30
Avco Corp
Liquid-metal-filled rotor blade

BE
BE794195D
patent/BE794195A/en
not_active
IP Right Cessation

1972

1972-01-18
CH
CH69972A
patent/CH547431A/en
not_active
IP Right Cessation

1972-01-21
DE
DE2202858A
patent/DE2202858C2/en
not_active
Expired

1973

1973-01-16
NL
NL7300634.A
patent/NL164358C/en
not_active
IP Right Cessation

1973-01-16
SE
SE7300582A
patent/SE381311B/en
unknown

1973-01-17
JP
JP48007731A
patent/JPS5145726B2/ja
not_active
Expired

1973-01-17
FR
FR7301574A
patent/FR2168802A5/fr
not_active
Expired

1973-01-17
GB
GB247973A
patent/GB1359983A/en
not_active
Expired

1973-01-17
CA
CA161,496A
patent/CA967095A/en
not_active
Expired

1973-01-18
US
US00324779A
patent/US3807892A/en
not_active
Expired – Lifetime

1973-01-18
IT
IT19321/73A
patent/IT978243B/en
active

Cited By (5)

* Cited by examiner, † Cited by third party

Publication number
Priority date
Publication date
Assignee
Title

GB2345942A
(en)

1998-12-24
2000-07-26
Rolls Royce Plc
Gas turbine engine blade cooling air system

EP1013882A3
(en)

1998-12-24
2001-12-05
Rolls-Royce Plc
Gas turbine engine internal air system

US6357999B1
(en)

1998-12-24
2002-03-19
Rolls-Royce Plc
Gas turbine engine internal air system

GB2345942B
(en)

1998-12-24
2002-08-07
Rolls Royce Plc
Gas turbine engine internal air system

GB2366600A
(en)

2000-09-09
2002-03-13
Rolls Royce Plc
Cooling arrangement for trailing edge of aerofoil

Also Published As

Publication number
Publication date

IT978243B
(en)

1974-09-20

CH547431A
(en)

1974-03-29

US3807892A
(en)

1974-04-30

NL7300634A
(en)

1973-07-20

NL164358B
(en)

1980-07-15

SE381311B
(en)

1975-12-01

FR2168802A5
(en)

1973-08-31

CA967095A
(en)

1975-05-06

JPS4882210A
(en)

1973-11-02

JPS5145726B2
(en)

1976-12-04

DE2202858B1
(en)

1973-07-26

DE2202858C2
(en)

1974-02-28

BE794195A
(en)

1973-07-18

NL164358C
(en)

1980-12-15

Contact information