GB1182687A - Creation of Inventions and Patents with Artificial Intelligence

GB1182687A – Improvements in or relating to Multiflow Jet Propulsion Engines
– Google Patents

GB1182687A – Improvements in or relating to Multiflow Jet Propulsion Engines
– Google Patents
Improvements in or relating to Multiflow Jet Propulsion Engines

Info

Publication number
GB1182687A

GB1182687A
GB32367/67A
GB3236767A
GB1182687A
GB 1182687 A
GB1182687 A
GB 1182687A
GB 32367/67 A
GB32367/67 A
GB 32367/67A
GB 3236767 A
GB3236767 A
GB 3236767A
GB 1182687 A
GB1182687 A
GB 1182687A
Authority
GB
United Kingdom
Prior art keywords
duct
nozzle
engine
air
gas turbine
Prior art date
1966-07-28
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
GB32367/67A
Inventor
Louis Jules Bauger
Armand Jean-Baptiste
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
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
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.)
1966-07-28
Filing date
1967-07-13
Publication date
1970-03-04

1967-07-13
Application filed by Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA, SNECMA SAS
filed
Critical
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA

1970-03-04
Publication of GB1182687A
publication
Critical
patent/GB1182687A/en

Status
Expired
legal-status
Critical
Current

Links

Espacenet

Global Dossier

Discuss

Classifications

F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING

F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS

F02K—JET-PROPULSION PLANTS

F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof

F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines

F02K7/16—Composite ram-jet/turbo-jet engines

F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING

F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS

F02K—JET-PROPULSION PLANTS

F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto

F02K1/06—Varying effective area of jet pipe or nozzle

F02K1/12—Varying effective area of jet pipe or nozzle by means of pivoted flaps

F02K1/1207—Varying effective area of jet pipe or nozzle by means of pivoted flaps of one series of flaps hinged at their upstream ends on a fixed structure

F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING

F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS

F02K—JET-PROPULSION PLANTS

F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan

F02K3/08—Plants including a gas turbine driving a compressor or a ducted fan with supplementary heating of the working fluid; Control thereof

F02K3/105—Heating the by-pass flow

F02K3/11—Heating the by-pass flow by means of burners or combustion chambers

Abstract

1,182,687. Gas turbine jet engines; ram jet engines. SOC. NATIONALE D’ETUDE ET DE CONSTRUCTION DE MOTEURS D’AVIATION. July 13, 1967 [July 28, 1966], No.32367/67. Heading F1J. The invention relates to a double flow jet propulsion engine comprising a gas turbine engine disposed in a central primary duct which is surrounded by an annular secondary duct. A combustion system is disposed in the secondary duct and a variable area nozzle is provided at the outlet of the secondary duct, the nozzle comprising angularly adjustable flaps pivotally mounted on the inner wall of the secondary duct. Means are provided for tapping off air from the secondary duct at a point upstream of the combustion system disposed therein, and for injecting this air downstream of the adjustable nozzle flaps in the turbulent region downstream thereof. The invention is shown applied in the case of a gas turbine bypass or ducted fan engine, the engine comprising an inner duct 1 in which are located compressor (not shown), combustion equipment 3 and turbine 4, the duct terminating in a propulsion nozzle 5. An outer, annular duct 2 surrounds the inner duct and receives air from the compressor or fan or from an intake diffuser, a combustion system 6 being provided in the duct, and the duct terminating in a variable area propulsion nozzle which is defined by a fixed outer wall and a series of angularly adjustable flaps 9 which are pivotally mounted at 9a at the downstream end of the inner wall of the annular duct. Air is tapped off from the outer duct at a point upstream of the combustion system 6, the air flowing through a duct 11 and being discharged into the turbulent region downstream of the nozzle 9. The air flowing through the duct 11 acts to cool parts such as the turbine casing 14 and the nozzle flap actuators 15, also accessories indicated at 13. In the case of an engine in which the outer duct is supplied directly from the intake, the outer duct thus constituting a ram jet engine, the gas turbine assembly may be shut down, the thrust being produced solely by the operation of the ram jet engine.

GB32367/67A
1966-07-28
1967-07-13
Improvements in or relating to Multiflow Jet Propulsion Engines

Expired

GB1182687A
(en)

Applications Claiming Priority (1)

Application Number
Priority Date
Filing Date
Title

FR71318A

FR1504543A
(en)

1966-07-28
1966-07-28

Improvements to turbojets and other bypass reactors

Publications (1)

Publication Number
Publication Date

GB1182687A
true

GB1182687A
(en)

1970-03-04

Family
ID=8614378
Family Applications (1)

Application Number
Title
Priority Date
Filing Date

GB32367/67A
Expired

GB1182687A
(en)

1966-07-28
1967-07-13
Improvements in or relating to Multiflow Jet Propulsion Engines

Country Status (3)

Country
Link

US
(1)

US3477230A
(en)

FR
(1)

FR1504543A
(en)

GB
(1)

GB1182687A
(en)

Cited By (2)

* Cited by examiner, † Cited by third party

Publication number
Priority date
Publication date
Assignee
Title

US9097140B2
(en)

2008-12-12
2015-08-04
Rolls-Royce Plc
Cavity ventilation

RU2746294C1
(en)

2020-02-28
2021-04-12
Публичное акционерное общество “ОДК – Уфимское моторостроительное производственное объединение” (ПАО “ОДК-УМПО”)
Two-engined aircraft power plant and power plant control method

Families Citing this family (13)

* Cited by examiner, † Cited by third party

Publication number
Priority date
Publication date
Assignee
Title

US3987621A
(en)

1974-06-03
1976-10-26
United Technologies Corporation
Method for reducing jet exhaust takeoff noise from a turbofan engine

US4185457A
(en)

1976-01-28
1980-01-29
United Technologies Corporation
Turbofan-ramjet engine

US5381655A
(en)

1993-05-10
1995-01-17
General Electric Company
Admission mixing duct assembly

WO2008045054A1
(en)

2006-10-12
2008-04-17
United Technologies Corporation
Modulating flow through gas turbine engine cooling system

EP2069629B1
(en)

2006-10-12
2014-09-24
United Technologies Corporation
Gas turbine engine fan variable area nozzle with swivalable insert system

WO2008045055A1
(en)

2006-10-12
2008-04-17
United Technologies Corporation
Turbofan engine having inner fixed structure including ducted passages

EP2074303B1
(en)

2006-10-12
2011-02-02
United Technologies Corporation
Core cowl airfoil for a gas turbine engine

FR2966435B1
(en)

2010-10-25
2013-04-26
Aircelle Sa

TURBO-BASE TRAILER WITH ADAPTABLE VENTILATION OUTPUT SECTION

US9045998B2
(en)

2011-12-12
2015-06-02
Honeywell International Inc.
System for directing air flow to a plurality of plena

US9267390B2
(en)

2012-03-22
2016-02-23
Honeywell International Inc.
Bi-metallic actuator for selectively controlling air flow between plena in a gas turbine engine

CN103726952B
(en)

2012-10-11
2016-07-13
高荣江
Shunting gas-turbine unit

US20160017815A1
(en)

2013-03-12
2016-01-21
United Technologies Corporation
Expanding shell flow control device

GB201609071D0
(en)

2016-05-24
2016-07-06
Rolls Royce Plc
Aircraft gas turbine engine nacelle

Family Cites Families (1)

* Cited by examiner, † Cited by third party

Publication number
Priority date
Publication date
Assignee
Title

US3269114A
(en)

1966-08-30

Marchant etal
j et propulsion engines

1966

1966-07-28
FR
FR71318A
patent/FR1504543A/en
not_active
Expired

1967

1967-07-13
GB
GB32367/67A
patent/GB1182687A/en
not_active
Expired

1967-07-24
US
US655529A
patent/US3477230A/en
not_active
Expired – Lifetime

Cited By (2)

* Cited by examiner, † Cited by third party

Publication number
Priority date
Publication date
Assignee
Title

US9097140B2
(en)

2008-12-12
2015-08-04
Rolls-Royce Plc
Cavity ventilation

RU2746294C1
(en)

Also Published As

Publication number
Publication date

US3477230A
(en)

1969-11-11

FR1504543A
(en)

1967-12-08

Contact information