GB2561188A - Increased efficiency reduced noise hypersonic aircraft propulsion - Google Patents

Increased efficiency reduced noise hypersonic aircraft propulsion Download PDF

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Publication number
GB2561188A
GB2561188A GB1705392.7A GB201705392A GB2561188A GB 2561188 A GB2561188 A GB 2561188A GB 201705392 A GB201705392 A GB 201705392A GB 2561188 A GB2561188 A GB 2561188A
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GB
United Kingdom
Prior art keywords
fan
turbofan engine
shaft power
bypass turbofan
high bypass
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.)
Withdrawn
Application number
GB1705392.7A
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GB201705392D0 (en
Inventor
Desmond Lewis Stephen
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Individual
Original Assignee
Individual
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 Individual filed Critical Individual
Priority to GB1705392.7A priority Critical patent/GB2561188A/en
Publication of GB201705392D0 publication Critical patent/GB201705392D0/en
Publication of GB2561188A publication Critical patent/GB2561188A/en
Withdrawn legal-status Critical Current

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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
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/107—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with two or more rotors connected by power transmission
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16D—COUPLINGS FOR TRANSMITTING ROTATION; CLUTCHES; BRAKES
    • F16D11/00—Clutches in which the members have interengaging parts
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/80—Application in supersonic vehicles excluding hypersonic vehicles or ram, scram or rocket propulsion

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)

Abstract

A turbofan engine 1 has a clutch enabling the fan 2 to be disconnected from the shaft allowing it to freely rotate. It may also be prevented from rotating by way of a brake. Preferably, the driveshaft to which the fan is connected is also connected to a generator 3 by a second clutch. The fan may be disconnected from the driveshaft at transonic speeds. The generator may be connected to the driveshaft at supersonic speeds.

Description

(54) Title of the Invention: Increased efficiency reduced noise hypersonic aircraft propulsion
Abstract Title: High bypass turbofan with fan and generator that can be disengaged from the driveshaft (57) A turbofan engine 1 has a clutch enabling the fan 2 to be disconnected from the shaft allowing it to freely rotate. It may also be prevented from rotating by way of a brake. Preferably, the driveshaft to which the fan is connected is also connected to a generator 3 by a second clutch. The fan may be disconnected from the driveshaft at transonic speeds. The generator may be connected to the driveshaft at supersonic speeds.
Figure GB2561188A_D0001
1/1
Figure GB2561188A_D0002
Figure 1
Increased efficiency reduced noise hypersonic aircraft propulsion
This invention relates to propulsion of a hypersonic aircraft or spaceplane at low speeds with reduced noise and increased efficiency.
This invention relates to generating electrical or mechanical energy from wind for a reduced cost.
To propel aircraft at Mach numbers high enough to enable ram/scramjets to operate turbojets need to have a high velocity exhaust to reach such speeds. This type of exhaust creates a large amount of noise on take-off which causes problems at airports and may limit where such a vehicle can fly. To overcome this, the present invention proposes a high bypass turbofan engine wherein clutch means disconnects shaft power from core of said high bypass turbofan engine to fan allowing said fan to freely rotate and/or be braked allowing thrust of engine to be produced by high velocity core exhaust.
On take-off the engine can produce thrust as a high bypass turbofan engine enabling improved efficiency over turbojets at low speeds, and with low amounts of noise. When an aircraft propelled by the engine has reached a sufficient speed and altitude which requires the performance of turbojets the disconnection of the fan enables the engine to operate as a turbojet combining the best of both engines.
Preferably, said shaft power forms part of a common power transmission to turn said fan and an electrical generator.
Preferably, said fan is disconnected from said shaft power at transonic speeds.
Preferably, said electrical generator is connected to said shaft power at supersonic speeds.
Preferably, said electrical generator is connected and disconnected to said shaft power by means of a second clutch.
An example of the invention will now be described by referring to the accompanying drawing:
- figure 1 shows a side view of the increased efficiency reduced noise hypersonic aircraft propulsion according to the invention.
A turbofan engine comprising of an engine core 1 and fan 2 operates as a turbofan engine at take-off and climb. Then at speeds which may be transonic the front fan of the turbofan engine is disconnected using clutch means from the shaft power of the engine core allowing the fan to freely rotate or to be braked. This allows the engine core to function as a turbojet engine to accelerate an aircraft using the engine to Mach numbers high enough to allow ram/scramjets to function. At speeds which may be supersonic an electrical generator 3 may be driven by the shaft power that may also turn the fan which may be connected and disconnected by a second clutch. This electrical generator can then heat air in a ram/scramjet 4 by creating electrical arcs using electrodes 5.
This enables an aircraft to take-off and climb with improved efficiency and low noise while still allowing supersonic flight to enable ram/scramjets to function. This makes the propulsion system more viable for commercial use in areas sensitive to noise.
Also an interesting feature of this is the ability to take-off as a turbofan or a turbojet allowing interesting displays at air shows and air displays.

Claims (5)

Claims
1 A high bypass turbofan engine wherein clutch means disconnects shaft power from core of said high bypass turbofan engine to fan allowing said fan to freely rotate and/or be braked allowing thrust of engine to be produced by high velocity core exhaust.
2 A high bypass turbofan engine according to claim 1, wherein said shaft power forms part of a common power transmission to turn said fan and an electrical generator.
3 A high bypass turbofan engine according to any of the preceding claims, wherein said fan is disconnected from said shaft power at transonic speeds.
4 A high bypass turbofan engine according to claim 2, wherein said electrical generator is connected to said shaft power at supersonic speeds.
5 A high bypass turbofan engine according to claims 2 and 4, wherein said electrical generator is connected and disconnected to said shaft power by means of a second clutch.
Intellectual
Property
Office
Application No: Claims searched:
GB1705392.7A 2017-04-04 2017-04-04 Increased efficiency reduced noise hypersonic aircraft propulsion Withdrawn GB2561188A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB1705392.7A GB2561188A (en) 2017-04-04 2017-04-04 Increased efficiency reduced noise hypersonic aircraft propulsion

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB1705392.7A GB2561188A (en) 2017-04-04 2017-04-04 Increased efficiency reduced noise hypersonic aircraft propulsion

Publications (2)

Publication Number Publication Date
GB201705392D0 GB201705392D0 (en) 2017-05-17
GB2561188A true GB2561188A (en) 2018-10-10

Family

ID=58682572

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1705392.7A Withdrawn GB2561188A (en) 2017-04-04 2017-04-04 Increased efficiency reduced noise hypersonic aircraft propulsion

Country Status (1)

Country Link
GB (1) GB2561188A (en)

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20060137355A1 (en) * 2004-12-27 2006-06-29 Pratt & Whitney Canada Corp. Fan driven emergency generator
US20060260323A1 (en) * 2005-05-19 2006-11-23 Djamal Moulebhar Aircraft with disengageable engine and auxiliary power unit components
JP2013194636A (en) * 2012-03-21 2013-09-30 Toyota Motor Corp Turboprop/fan type jet engine with clutch
US20160003143A1 (en) * 2013-02-26 2016-01-07 United Technologies Corporation Turbomachine fan clutch
US9605557B1 (en) * 2013-04-30 2017-03-28 United States Of America As Represented By The Secretary Of The Air Force Variable bypass turbofan engine

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20060137355A1 (en) * 2004-12-27 2006-06-29 Pratt & Whitney Canada Corp. Fan driven emergency generator
US20060260323A1 (en) * 2005-05-19 2006-11-23 Djamal Moulebhar Aircraft with disengageable engine and auxiliary power unit components
JP2013194636A (en) * 2012-03-21 2013-09-30 Toyota Motor Corp Turboprop/fan type jet engine with clutch
US20160003143A1 (en) * 2013-02-26 2016-01-07 United Technologies Corporation Turbomachine fan clutch
US9605557B1 (en) * 2013-04-30 2017-03-28 United States Of America As Represented By The Secretary Of The Air Force Variable bypass turbofan engine

Also Published As

Publication number Publication date
GB201705392D0 (en) 2017-05-17

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WAP Application withdrawn, taken to be withdrawn or refused ** after publication under section 16(1)