GB1439988A - Creation of Inventions and Patents with Artificial Intelligence

GB1439988A – Turbojet engine
– Google Patents

GB1439988A – Turbojet engine
– Google Patents
Turbojet engine

Info

Publication number
GB1439988A

GB1439988A
GB3989073A
GB3989073A
GB1439988A
GB 1439988 A
GB1439988 A
GB 1439988A
GB 3989073 A
GB3989073 A
GB 3989073A
GB 3989073 A
GB3989073 A
GB 3989073A
GB 1439988 A
GB1439988 A
GB 1439988A
Authority
GB
United Kingdom
Prior art keywords
turbine
fan
gases
flaps
drive
Prior art date
1972-08-26
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
GB3989073A
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.)

MTU Aero Engines GmbH

Original Assignee
MTU Motoren und Turbinen Union Muenchen GmbH
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.)
1972-08-26
Filing date
1973-08-22
Publication date
1976-06-16

1973-08-22
Application filed by MTU Motoren und Turbinen Union Muenchen GmbH
filed
Critical
MTU Motoren und Turbinen Union Muenchen GmbH

1976-06-16
Publication of GB1439988A
publication
Critical
patent/GB1439988A/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

F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS

F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas- turbine plants for special use

F02C6/20—Adaptations of gas-turbine plants for driving vehicles

F02C6/206—Adaptations of gas-turbine plants for driving vehicles the vehicles being airscrew driven

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

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

F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS

F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants

F02C9/16—Control of working fluid flow

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

F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber

F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type

F02K3/06—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan

Abstract

1439988 Driving helicopter rotors MOTOREN UND TURBINEN-UNION MUNCHEN GmbH 22 Aug 1973 [26 Aug 1972] 39890/73 Heading B7G [Also in Division F1] The invention relates to a gas turbine engine of the ducted fan type in which a separate power turbine is provided and which is connected through gearing to drive a helicopter lift rotor, control means being provided whereby gases may be directed either to the turbine driving the ducted fan so giving forward thrust, or to the power turbine driving the lift rotor so giving vertical lift. The engine shown in Fig. 1 comprises a fan 1, HP compressor 2, combustion equipment 4, HP turbine 5 which drives the HP compressor 2 through outer shaft 11, LP turbine 6 which drives the fan through shaft 7, also a separate power turbine 19. The fan rotor comprises pivotally mounted blades 13 disposed within the fan duct and fixed blades 17 mounted within the inlet duct to the HP compressor. Pivotally-mounted inlet guide vanes 25 are provided for the LP turbine and pivotallymounted inlet guide vanes 26 for the power turbine 19. A series of pivotally-mounted flaps 261 are disposed adjacent the IGV’s 25 such that when the flaps are in the outer position gases discharging from the HP turbine are directed to the LP turbine 6 which drives the ducted fan 1, the gases then discharging through the passage 27 to the propulsion nozzle 18; thus in this mode the engine provides forward thrust. When the flaps 261 are moved to their inner position the gases from the HP turbine are prevented from passing to the LP turbine, thus the ducted fan is not driven; instead the gases pass through the passage 28 through the IGV’s 26 on to the power turbine 19 which is thereby driven and acts to drive the lift rotor 23 through gearing 21; thus in this mode the engine provides vertical lift. The controls are arranged to provide smooth transition from vertical to forward thrust and vice versa. In a second embodiment in place of the pivoted flaps 261 and IGV’s 25, 26, two axially-slidable ring valves are provided which permit gas flow from the HP turbine either through the LP turbine to drive the ducted fan or through the power turbine to drive the lift rotor. The blades of the lift rotor are of variable pitch, the pitch being increased as the pitch of the fan blades is reduced, and vice versa.

GB3989073A
1972-08-26
1973-08-22
Turbojet engine

Expired

GB1439988A
(en)

Applications Claiming Priority (1)

Application Number
Priority Date
Filing Date
Title

DE19722242048

DE2242048A1
(en)

1972-08-26
1972-08-26

TURBINE JET IN MULTI-FLOW AND MULTI-SHAFT DESIGN

Publications (1)

Publication Number
Publication Date

GB1439988A
true

GB1439988A
(en)

1976-06-16

Family
ID=5854627
Family Applications (1)

Application Number
Title
Priority Date
Filing Date

GB3989073A
Expired

GB1439988A
(en)

1972-08-26
1973-08-22
Turbojet engine

Country Status (3)

Country
Link

DE
(1)

DE2242048A1
(en)

FR
(1)

FR2197116B3
(en)

GB
(1)

GB1439988A
(en)

Cited By (5)

* Cited by examiner, † Cited by third party

Publication number
Priority date
Publication date
Assignee
Title

US4791783A
(en)

1981-11-27
1988-12-20
General Electric Company
Convertible aircraft engine

CN109279002A
(en)

2017-07-21
2019-01-29
通用电气公司
The VTOL vehicles of fan blade with discharge flow path external

CN113864082A
(en)

2021-09-13
2021-12-31
上海新云彩航空科技有限责任公司
Aviation jet engine

EP4283105A1
(en)

2022-05-26
2023-11-29
RTX Corporation
Aircraft propulsion system with variable speed rotating structure

EP4282764A1
(en)

2022-05-26
2023-11-29
RTX Corporation
Aircraft propulsion system with adjustable thrust propulsor

Families Citing this family (4)

* Cited by examiner, † Cited by third party

Publication number
Priority date
Publication date
Assignee
Title

US5003766A
(en)

1984-10-10
1991-04-02
Paul Marius A
Gas turbine engine

AU5201486A
(en)

1984-10-10
1986-05-02
Paul, M.A.
Gas turbine engine

US4936748A
(en)

1988-11-28
1990-06-26
General Electric Company
Auxiliary power source in an unducted fan gas turbine engine

CN111137082A
(en)

2019-12-30
2020-05-12
长春理工大学
Single-duct land air cross-domain robot and control method thereof

1972

1972-08-26
DE
DE19722242048
patent/DE2242048A1/en
active
Pending

1973

1973-08-22
GB
GB3989073A
patent/GB1439988A/en
not_active
Expired

1973-08-24
FR
FR7330806A
patent/FR2197116B3/fr
not_active
Expired

Cited By (7)

* Cited by examiner, † Cited by third party

Publication number
Priority date
Publication date
Assignee
Title

US4791783A
(en)

1981-11-27
1988-12-20
General Electric Company
Convertible aircraft engine

CN109279002A
(en)

2017-07-21
2019-01-29
通用电气公司
The VTOL vehicles of fan blade with discharge flow path external

CN109279002B
(en)

2017-07-21
2022-07-05
通用电气公司
VTOL vehicles with fan blades outside of the exhaust flow path

CN113864082A
(en)

2021-09-13
2021-12-31
上海新云彩航空科技有限责任公司
Aviation jet engine

CN113864082B
(en)

2021-09-13
2022-12-06
上海新云彩航空科技有限责任公司
Aviation jet engine

EP4283105A1
(en)

2022-05-26
2023-11-29
RTX Corporation
Aircraft propulsion system with variable speed rotating structure

EP4282764A1
(en)

2022-05-26
2023-11-29
RTX Corporation
Aircraft propulsion system with adjustable thrust propulsor

Also Published As

Publication number
Publication date

DE2242048A1
(en)

1974-03-07

FR2197116B3
(en)

1976-07-30

FR2197116A1
(en)

1974-03-22

Contact information