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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
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 AG
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.)
Filing date
Publication date
Application filed by MTU Motoren und Turbinen Union Muenchen GmbH filed Critical MTU Motoren und Turbinen Union Muenchen GmbH
Publication of GB1439988A publication Critical patent/GB1439988A/en
Expired legal-status Critical Current

Links

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

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Control Of Turbines (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

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 26<SP>1</SP> 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 26<SP>1</SP> 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 26<SP>1</SP> 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 (8)

* 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 VTOL vehicle with fan blades outside the discharge 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
CN116517688A (en) * 2023-03-21 2023-08-01 南京航空航天大学 Turbine shaft turbojet variable cycle engine scheme
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
US12135076B1 (en) 2023-09-29 2024-11-05 Rtx Corporation Fluid device(s) for supporting rotating structure(s) of a turbine engine
US12188551B1 (en) 2023-09-29 2025-01-07 Rtx Corporation Reduced clearance interface between a fluid device and a rotating structure for a geartrain

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS62501304A (en) * 1984-10-10 1987-05-21 ポ−ル　マリウス　エイ gas turbine engine
US5003766A (en) * 1984-10-10 1991-04-02 Paul Marius 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

Cited By (11)

* 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 VTOL vehicle with fan blades outside the discharge flow path
CN109279002B (en) * 2017-07-21 2022-07-05 通用电气公司 VTOL vehicle with fan blades outside the discharge 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
CN116517688A (en) * 2023-03-21 2023-08-01 南京航空航天大学 Turbine shaft turbojet variable cycle engine scheme
CN116517688B (en) * 2023-03-21 2024-09-06 南京航空航天大学 A turboshaft turbojet variable cycle engine scheme
US12135076B1 (en) 2023-09-29 2024-11-05 Rtx Corporation Fluid device(s) for supporting rotating structure(s) of a turbine engine
US12188551B1 (en) 2023-09-29 2025-01-07 Rtx Corporation Reduced clearance interface between a fluid device and a rotating structure for a geartrain

Also Published As

Publication number Publication date
FR2197116B3 (en) 1976-07-30
DE2242048A1 (en) 1974-03-07
FR2197116A1 (en) 1974-03-22

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Legal Events

Date Code Title Description
PS Patent sealed
PLNP Patent lapsed through nonpayment of renewal fees