GB1444679A – After-burner fuel injection devices for jet engines
– Google Patents
GB1444679A – After-burner fuel injection devices for jet engines
– Google Patents
After-burner fuel injection devices for jet engines
Info
Publication number
GB1444679A
GB1444679A
GB1785874A
GB1785874A
GB1444679A
GB 1444679 A
GB1444679 A
GB 1444679A
GB 1785874 A
GB1785874 A
GB 1785874A
GB 1785874 A
GB1785874 A
GB 1785874A
GB 1444679 A
GB1444679 A
GB 1444679A
Authority
GB
United Kingdom
Prior art keywords
sleeve
duct
april
passing
pipe
Prior art date
1973-04-27
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
GB1785874A
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.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA SAS
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.)
1973-04-27
Filing date
1974-04-24
Publication date
1976-08-04
1974-04-24
Application filed by SNECMA SAS
filed
Critical
SNECMA SAS
1976-08-04
Publication of GB1444679A
publication
Critical
patent/GB1444679A/en
Status
Expired
legal-status
Critical
Current
Links
Espacenet
Global Dossier
Discuss
239000000446
fuel
Substances
0.000
title
abstract
2
238000002347
injection
Methods
0.000
title
1
239000007924
injection
Substances
0.000
title
1
238000002485
combustion reaction
Methods
0.000
abstract
1
238000010276
construction
Methods
0.000
abstract
1
238000006073
displacement reaction
Methods
0.000
abstract
1
210000002445
nipple
Anatomy
0.000
abstract
1
238000007789
sealing
Methods
0.000
abstract
1
230000008646
thermal stress
Effects
0.000
abstract
1
Classifications
F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
F23R3/20—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants incorporating fuel injection means
F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
Abstract
1444679 Sealing pipes to walls SOC NATIONALE D’ETUDE ET DE CONSTRUCTION DE MOTEURS D’AVIATION 24 April 1974 [27 April 1973] 17858/74 Heading F2G [Also in Division F1] To reduce thermal stresses, a fuel pipe 15 is slidably mounted within a wall member 33 which is itself movable substantially axially of reheat combustion duct 5. The end of pipe 15 is welded to a flared ferrule 15c engaging a nipple 15d on the end of a feed pipe 26 external of duct 5, the connection being sealingly maintained by a threaded ring 27 screwed within a sleeve 28. The latter and ring 27 are locked together by external teeth 28d, 27b thereon engaging splines within a sleeve 30, a U-shaped locking pin 31 passing through sleeve 30 and between the two sets of teeth. Sleeve 28 is slidable within the bore 33c of wall member 33 which is itself pivoted about a bolt 34 passing through hole 33f and secured to a flat 5b on duct 5. Member 33 is thus capable of small angular displacements α within circular opening 5a in a direction generally axially of duct 5.
GB1785874A
1973-04-27
1974-04-24
After-burner fuel injection devices for jet engines
Expired
GB1444679A
(en)
Applications Claiming Priority (1)
Application Number
Priority Date
Filing Date
Title
FR7315347A
FR2227436B1
(en)
1973-04-27
1973-04-27
Publications (1)
Publication Number
Publication Date
GB1444679A
true
GB1444679A
(en)
1976-08-04
Family
ID=9118583
Family Applications (1)
Application Number
Title
Priority Date
Filing Date
GB1785874A
Expired
GB1444679A
(en)
1973-04-27
1974-04-24
After-burner fuel injection devices for jet engines
Country Status (4)
Country
Link
US
(1)
US3910038A
(en)
DE
(1)
DE2419929C3
(en)
FR
(1)
FR2227436B1
(en)
GB
(1)
GB1444679A
(en)
Cited By (1)
* Cited by examiner, † Cited by third party
Publication number
Priority date
Publication date
Assignee
Title
EP1741983A3
(en)
*
2005-06-30
2009-09-09
United Technologies Corporation
Augmentor spray bars
Families Citing this family (5)
* Cited by examiner, † Cited by third party
Publication number
Priority date
Publication date
Assignee
Title
US4185462A
(en)
*
1978-04-05
1980-01-29
General Electric Company
Fluid fitting for turbofan engines
FR2551500B1
(en)
*
1983-09-07
1985-11-08
Snecma
BURNER RING FOR POSTCOMBUSTION OF A REACTION ENGINE
US5001897A
(en)
*
1989-12-20
1991-03-26
United Technologies Corporation
Augmentor spray ring mount
US10077741B2
(en)
2012-05-29
2018-09-18
United Technologies Corporation
Spraybar face seal retention arrangement
US10436448B2
(en)
*
2015-12-16
2019-10-08
Delavan Inc.
Injector fittings
Family Cites Families (5)
* Cited by examiner, † Cited by third party
Publication number
Priority date
Publication date
Assignee
Title
US2780916A
(en)
*
1952-08-22
1957-02-12
Continental Aviat & Engineerin
Pilot burner for jet engines
US3210928A
(en)
*
1960-08-19
1965-10-12
Joseph J Zelinski
Fuel cooled combustor assembly
US3153324A
(en)
*
1963-05-29
1964-10-20
Robert E Meyer
Simplified primary fuel system
US3269116A
(en)
*
1965-04-29
1966-08-30
United Aircraft Corp
Centrally supported flameholder
US3572733A
(en)
*
1969-01-02
1971-03-30
Gen Electric
Shaft seal used in gas turbine engines
1973
1973-04-27
FR
FR7315347A
patent/FR2227436B1/fr
not_active
Expired
1974
1974-04-24
GB
GB1785874A
patent/GB1444679A/en
not_active
Expired
1974-04-25
DE
DE2419929A
patent/DE2419929C3/en
not_active
Expired
1974-04-26
US
US464451A
patent/US3910038A/en
not_active
Expired – Lifetime
Cited By (2)
* Cited by examiner, † Cited by third party
Publication number
Priority date
Publication date
Assignee
Title
EP1741983A3
(en)
*
2005-06-30
2009-09-09
United Technologies Corporation
Augmentor spray bars
US7647775B2
(en)
2005-06-30
2010-01-19
United Technologies Corporation
Augmentor spray bars
Also Published As
Publication number
Publication date
DE2419929B2
(en)
1979-04-12
DE2419929A1
(en)
1974-11-07
FR2227436A1
(en)
1974-11-22
FR2227436B1
(en)
1975-12-26
DE2419929C3
(en)
1979-12-06
US3910038A
(en)
1975-10-07
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Legal Events
Date
Code
Title
Description
1976-12-15
PS
Patent sealed [section 19, patents act 1949]
1992-12-23
PCNP
Patent ceased through non-payment of renewal fee
