GB1445015A – Gas turbine engines
– Google Patents
GB1445015A – Gas turbine engines
– Google Patents
Gas turbine engines
Info
Publication number
GB1445015A
GB1445015A
GB5732673A
GB5732673A
GB1445015A
GB 1445015 A
GB1445015 A
GB 1445015A
GB 5732673 A
GB5732673 A
GB 5732673A
GB 5732673 A
GB5732673 A
GB 5732673A
GB 1445015 A
GB1445015 A
GB 1445015A
Authority
GB
United Kingdom
Prior art keywords
shaft
engine
turbine
power
drive
Prior art date
1972-12-26
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
GB5732673A
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.)
1972-12-26
Filing date
1973-12-11
Publication date
1976-08-04
1973-12-11
Application filed by General Electric Co
filed
Critical
General Electric Co
1976-08-04
Publication of GB1445015A
publication
Critical
patent/GB1445015A/en
Status
Expired
legal-status
Critical
Current
Links
Espacenet
Global Dossier
Discuss
230000000712
assembly
Effects
0.000
abstract
1
238000000429
assembly
Methods
0.000
abstract
1
238000002485
combustion reaction
Methods
0.000
abstract
1
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
F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
F01D25/285—Temporary support structures, e.g. for testing, assembling, installing, repairing; Assembly methods using such structures
Abstract
1445015 Gas turbine engines – power turbine modules GENERAL ELECTRIC CO 11 Dec 1973 [26 Dec 1972] 57326/73 Headings F1G and F1J The invention relates to a gas turbine engine of the kind having a separate power turbine, the drive shaft of the power turbine extending forwardly through the engine and engaging at its forward end with a power take-off shaft, the power turbine being in the form of a module which is releasable and removable from the remainder of the engine in an axially rearward direction. The engine shown comprises a compressor 16, combustion equipment 28, an H.P. turbine 36 connected to drive the compressor through hollow shaft 38, and an L.P. power turbine 40 connected to a hollow drive-shaft 42 which extends forwardly through the engine, through the hollow shaft 38, being connected at its forward end to a power take-off shaft 43 through a spline connection 164. The power take-off shaft is in turn connected at its forward end to an output shaft 171 through a spline connection 173. The output shaft may be connected to drive a helicopter lift rotor, a ducted fan or an airscrew. The engine comprises a front frame 45 within which the power take-off shaft is rotatably mounted by means of a roller bearing 166, also by means of a double-row ball thrust bearing 174, 180. The frame 45 also carries a bearing 48 which supports the forward end of the compressor/turbine shaft. The engine comprises also a rear frame 47 which carries a roller bearing 152 which supports the rearward end of the drive-shaft 42; the rearward end of the shaft is also supported by means of a ball thrust bearing 158. The rearward end of the compressor/turbine shaft 38 is supported in a roller bearing 50 carried by engine stator structure (46). The power turbine comprises an outer stator casing 100 which carries the power turbine inlet nozzle guide vane assembly 120 and inter-stage guide vane assembly 106, also shroud structure 96, 98 for the rotor blade assemblies 84, 88, the stator casing 100 being secured to the engine stator casing 12 by means of releasable bolts 103. By releasing the bolts 103, the power turbine module including the driveshaft 42 may be removed from the engine in an axially rearward direction. The spline connections 164 and 173 are lubricated by means of an oil supply nozzle 186 which supplies oil through inclined openings 188 in the power take-off shaft 43, the oil passing through the splines thence through openings 193, 193′ in dams 192, 192′. The output torque is measured by means of a meter comprising a tube 163 secured within the hollow drive-shaft 42.
GB5732673A
1972-12-26
1973-12-11
Gas turbine engines
Expired
GB1445015A
(en)
Applications Claiming Priority (1)
Application Number
Priority Date
Filing Date
Title
US00318280A
US3823553A
(en)
1972-12-26
1972-12-26
Gas turbine with removable self contained power turbine module
Publications (1)
Publication Number
Publication Date
GB1445015A
true
GB1445015A
(en)
1976-08-04
Family
ID=23237476
Family Applications (1)
Application Number
Title
Priority Date
Filing Date
GB5732673A
Expired
GB1445015A
(en)
1972-12-26
1973-12-11
Gas turbine engines
Country Status (8)
Country
Link
US
(1)
US3823553A
(en)
JP
(1)
JPS5727292B2
(en)
BE
(1)
BE809056A
(en)
CA
(1)
CA986731A
(en)
DE
(1)
DE2364431C2
(en)
FR
(1)
FR2211589B1
(en)
GB
(1)
GB1445015A
(en)
IT
(1)
IT1002233B
(en)
Cited By (3)
* Cited by examiner, † Cited by third party
Publication number
Priority date
Publication date
Assignee
Title
DE3041157A1
(en)
*
1979-11-03
1981-05-07
Rolls-Royce Ltd., London
GAS TURBINE ENGINE
GB2219046A
(en)
*
1988-05-13
1989-11-29
United Technologies Corp
Disassembly of a modular fan gas turbine engine
US20220290617A1
(en)
*
2019-09-27
2022-09-15
Safran Aircraft Engines
Turbomachine fan assembly comprising a roller bearing and a double-row ball bearing with oblique contact
Families Citing this family (48)
* Cited by examiner, † Cited by third party
Publication number
Priority date
Publication date
Assignee
Title
GB1438195A
(en)
*
1973-08-08
1976-06-03
Penny Turbines Ltd Noel
Mounting for attaching a tubular member in co-axial registration with an aperture in a wall
DE2525950A1
(en)
*
1975-06-11
1976-12-16
Motoren Turbinen Union
MODULAR GAS TURBINE ENGINE
US4030288A
(en)
*
1975-11-10
1977-06-21
Caterpillar Tractor Co.
Modular gas turbine engine assembly
US4083180A
(en)
*
1976-10-01
1978-04-11
Caterpillar Tractor Co.
Gas turbine engine internal insulation
US4201426A
(en)
*
1978-04-27
1980-05-06
General Electric Company
Bearing clamping assembly for a gas turbine engine
US4592204A
(en)
*
1978-10-26
1986-06-03
Rice Ivan G
Compression intercooled high cycle pressure ratio gas generator for combined cycles
US4251987A
(en)
*
1979-08-22
1981-02-24
General Electric Company
Differential geared engine
JPS5644426A
(en)
*
1979-09-14
1981-04-23
Ngk Spark Plug Co Ltd
Supercharger
FR2544387B1
(en)
*
1983-04-15
1985-06-14
Snecma
APPARATUS FOR TRANSFERRING A FULL TURBINE MODULE FROM A BALANCING MACHINE TO A MOTOR AND VICE VERSA, AND METHOD FOR OPERATING SAID APPARATUS
US4685286A
(en)
*
1984-05-02
1987-08-11
United Technologies Corporation
Method of disassembly for a gas turbine engine
US4611464A
(en)
*
1984-05-02
1986-09-16
United Technologies Corporation
Rotor assembly for a gas turbine engine and method of disassembly
US4728255A
(en)
*
1985-02-25
1988-03-01
General Electric Company
Removable stiffening disk
DE3614182A1
(en)
*
1985-04-29
1986-11-06
Teledyne Industries, Inc., Los Angeles, Calif.
TURBINE
JPS6296399U
(en)
*
1985-12-07
1987-06-19
US4744214A
(en)
*
1987-06-29
1988-05-17
United Technologies Corporation
Engine modularity
FR2644844B1
(en)
*
1989-03-23
1994-05-06
Snecma
SUSPENSION OF THE LOW PRESSURE TURBINE ROTOR OF A DOUBLE BODY TURBOMACHINE
US5205513A
(en)
*
1991-09-26
1993-04-27
General Electric Company
Method and system for the removal of large turbine engines
US5226788A
(en)
*
1991-12-23
1993-07-13
General Electric Company
Turbine heat shield and bolt retainer assembly
US5211541A
(en)
1991-12-23
1993-05-18
General Electric Company
Turbine support assembly including turbine heat shield and bolt retainer assembly
US5537814A
(en)
*
1994-09-28
1996-07-23
General Electric Company
High pressure gas generator rotor tie rod system for gas turbine engine
EP0844369B1
(en)
*
1996-11-23
2002-01-30
ROLLS-ROYCE plc
A bladed rotor and surround assembly
US6053697A
(en)
*
1998-06-26
2000-04-25
General Electric Company
Trilobe mounting with anti-rotation apparatus for an air duct in a gas turbine rotor
SE519323C2
(en)
*
2001-06-28
2003-02-11
Volvo Aero Ab
Modular gas turbine
US7409819B2
(en)
*
2004-10-29
2008-08-12
General Electric Company
Gas turbine engine and method of assembling same
GB0502324D0
(en)
*
2005-03-14
2005-03-16
Rolls Royce Plc
A multi-shaft arrangement for a turbine engine
US7510371B2
(en)
*
2005-06-06
2009-03-31
General Electric Company
Forward tilted turbine nozzle
US7594388B2
(en)
*
2005-06-06
2009-09-29
General Electric Company
Counterrotating turbofan engine
US7513102B2
(en)
*
2005-06-06
2009-04-07
General Electric Company
Integrated counterrotating turbofan
FR2889561B1
(en)
*
2005-08-02
2010-10-29
Snecma
SYSTEM FOR SEALING THE REAR LUBRICATION CHAMBER FROM A TURBOJET ENGINE
US20070220895A1
(en)
*
2005-09-19
2007-09-27
General Electric Company
Methods and apparatus for housing gas turbine engines
FR2906846B1
(en)
*
2006-10-06
2008-12-26
Snecma Sa
CHANNEL TRANSITION BETWEEN TWO TURBINE STAGES
US8162605B2
(en)
*
2008-01-14
2012-04-24
United Technologies Corporation
Gas turbine engine case
FR2932227B1
(en)
*
2008-06-09
2011-07-01
Snecma
TURBOJET DOUBLE FLOW
FR2944558B1
(en)
*
2009-04-17
2014-05-02
Snecma
DOUBLE BODY GAS TURBINE ENGINE PROVIDED WITH SUPPLEMENTARY BP TURBINE BEARING.
US8459943B2
(en)
*
2010-03-10
2013-06-11
United Technologies Corporation
Gas turbine engine rotor sections held together by tie shaft, and with blade rim undercut
US8517687B2
(en)
*
2010-03-10
2013-08-27
United Technologies Corporation
Gas turbine engine compressor and turbine section assembly utilizing tie shaft
US20110219781A1
(en)
*
2010-03-10
2011-09-15
Daniel Benjamin
Gas turbine engine with tie shaft for axial high pressure compressor rotor
US20110219784A1
(en)
*
2010-03-10
2011-09-15
St Mary Christopher
Compressor section with tie shaft coupling and cantilever mounted vanes
US9212557B2
(en)
2011-08-31
2015-12-15
United Technologies Corporation
Assembly and method preventing tie shaft unwinding
US8932011B2
(en)
*
2011-10-06
2015-01-13
United Technologies Corporation
Shaft assembly for a gas turbine engine
US20130156584A1
(en)
*
2011-12-16
2013-06-20
Carney R. Anderson
Compressor rotor with internal stiffening ring of distinct material
US20130340435A1
(en)
*
2012-01-31
2013-12-26
Gregory M. Savela
Gas turbine engine aft spool bearing arrangement and hub wall configuration
US20130195647A1
(en)
*
2012-01-31
2013-08-01
Marc J. Muldoon
Gas turbine engine bearing arrangement including aft bearing hub geometry
US9476320B2
(en)
2012-01-31
2016-10-25
United Technologies Corporation
Gas turbine engine aft bearing arrangement
EP2900941B1
(en)
2012-09-26
2016-12-14
United Technologies Corporation
Combined high pressure turbine case and turbine intermediate case
US9598981B2
(en)
*
2013-11-22
2017-03-21
Siemens Energy, Inc.
Industrial gas turbine exhaust system diffuser inlet lip
CN108223429B
(en)
*
2017-09-30
2021-03-30
中国航发沈阳发动机研究所
Whole ring fan casing without breaking disc
US11725542B2
(en)
2021-07-29
2023-08-15
Pratt & Whitney Canada Corp.
Gas turbine engine disassembly / assembly methods
Family Cites Families (11)
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Publication date
Assignee
Title
US2444363A
(en)
*
1944-08-30
1948-06-29
United Aircraft Corp
Helical spline torque indicator
US2747367A
(en)
*
1950-03-21
1956-05-29
United Aircraft Corp
Gas turbine power plant supporting structure
US2757857A
(en)
*
1951-06-19
1956-08-07
United Aircraft Corp
Locking means between compressor and turbine
US2862356A
(en)
*
1954-07-16
1958-12-02
Rolls Royce
Bearing arrangements for gas-turbine engines
US2971334A
(en)
*
1955-01-04
1961-02-14
Solar Aircraft Co
Gas turbine engine adaptable for multi-purpose use
US2851246A
(en)
*
1956-10-24
1958-09-09
United Aircraft Corp
Turbine or compressor construction and method of assembly
US2916874A
(en)
*
1957-01-31
1959-12-15
United Aircraft Corp
Engine construction
DE1128706B
(en)
*
1957-05-01
1962-04-26
Avco Mfg Corp
Gas turbine system with a drive shaft of the power turbine extending through the compressor drive turbine
US3088278A
(en)
*
1957-05-01
1963-05-07
Avco Mfg Corp
Gas turbine engine
GB846329A
(en)
*
1957-12-12
1960-08-31
Napier & Son Ltd
Combustion turbine power units
GB1139941A
(en)
*
1965-03-30
1969-01-15
Rolls Royce
Engine drive
1972
1972-12-26
US
US00318280A
patent/US3823553A/en
not_active
Expired – Lifetime
1973
1973-12-06
CA
CA187,489A
patent/CA986731A/en
not_active
Expired
1973-12-10
IT
IT32080/73A
patent/IT1002233B/en
active
1973-12-11
GB
GB5732673A
patent/GB1445015A/en
not_active
Expired
1973-12-21
JP
JP14256473A
patent/JPS5727292B2/ja
not_active
Expired
1973-12-21
BE
BE139242A
patent/BE809056A/en
unknown
1973-12-22
DE
DE2364431A
patent/DE2364431C2/en
not_active
Expired
1973-12-26
FR
FR7346207A
patent/FR2211589B1/fr
not_active
Expired
Cited By (3)
* Cited by examiner, † Cited by third party
Publication number
Priority date
Publication date
Assignee
Title
DE3041157A1
(en)
*
1979-11-03
1981-05-07
Rolls-Royce Ltd., London
GAS TURBINE ENGINE
GB2219046A
(en)
*
1988-05-13
1989-11-29
United Technologies Corp
Disassembly of a modular fan gas turbine engine
US20220290617A1
(en)
*
2019-09-27
2022-09-15
Safran Aircraft Engines
Turbomachine fan assembly comprising a roller bearing and a double-row ball bearing with oblique contact
Also Published As
Publication number
Publication date
BE809056A
(en)
1974-04-16
FR2211589A1
(en)
1974-07-19
CA986731A
(en)
1976-04-06
JPS4996112A
(en)
1974-09-11
DE2364431C2
(en)
1984-04-19
JPS5727292B2
(en)
1982-06-09
US3823553A
(en)
1974-07-16
IT1002233B
(en)
1976-05-20
FR2211589B1
(en)
1980-09-05
DE2364431A1
(en)
1974-06-27
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Legal Events
Date
Code
Title
Description
1976-12-15
PS
Patent sealed [section 19, patents act 1949]
1981-04-15
746
Register noted ‘licences of right’ (sect. 46/1977)
1994-01-12
PE20
Patent expired after termination of 20 years
Effective date:
19931210
