[go: up one dir, main page]

US20050284129A1 - Hybrid propulsion system - Google Patents

Hybrid propulsion system Download PDF

Info

Publication number
US20050284129A1
US20050284129A1 US10/876,355 US87635504A US2005284129A1 US 20050284129 A1 US20050284129 A1 US 20050284129A1 US 87635504 A US87635504 A US 87635504A US 2005284129 A1 US2005284129 A1 US 2005284129A1
Authority
US
United States
Prior art keywords
oxygen
engine
gate
burner
propulsion system
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.)
Granted
Application number
US10/876,355
Other versions
US6973774B1 (en
Inventor
Robert Wood
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.)
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 US10/876,355 priority Critical patent/US6973774B1/en
Application granted granted Critical
Publication of US6973774B1 publication Critical patent/US6973774B1/en
Publication of US20050284129A1 publication Critical patent/US20050284129A1/en
Adjusted expiration legal-status Critical
Expired - Fee Related legal-status Critical Current

Links

Images

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
    • F02C6/18—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use using the waste heat of gas-turbine plants outside the plants themselves, e.g. gas-turbine power heat plants
    • 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

Definitions

  • This invention pertains to the field of aerospace propulsion systems. Presently, the altitude to which an aircraft can ascend is limited by the lack of oxygen in the atmosphere. This invention is intended to solve the particular problem.
  • the object of this invention is to enable an air breathing engine to perform at much higher altitudes that are currently unattainable. This is achieved by augmenting the oxygen with an “on board” supply of cryogenic oxygen.
  • FIG. 1 is a general arrangement which shows a generic jet engine at the core of the system.
  • the drawing illustrates the modified after burner section, now modified to vaporize liquid oxygen, which in turn is used as a coolant for the after burner sheet metal.
  • the gate is shown, deflecting the vaporized oxygen into the intake.
  • the elements of a control system which link the gate aperture to the motor driving the cryogenic pump.
  • liquid oxygen is pumped into the evaporator which consists of a helical coil wrapped around the cylindrical after burner.
  • the cross-section of the coil expands progressively to accommodate the expanding oxygen.
  • the evaporator coils stop at the turbine section where it becomes a straight duct on the topside of the engine.
  • the vaporized oxygen now passes through an opening in the top of the rectangular intake and is deflected towards the compressor section of the engine.
  • ambient air is also admitted.
  • the air/oxygen mix passes through the compressors into the combustors where fuel is sprayed in to maintain the flame front.
  • the oxygen rich exhaust stream then enters the after burner where more fuel is added to further increase thrust.
  • the gate gradually closes off the air intake, and the system continues to run on pure oxygen. Beyond the atmosphere, the exhaust stream is vectored for steering purposes

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)

Abstract

Whilst commercial jet aircraft are capable of transporting large pay load economically, the same is not true for rockets. To solve this problem, a hybrid propulsion system is proposed for use in Horizontal Take-Off and Land (HOTOL) craft. The purpose is to maximized the use of ambient oxygen and minimize the use of cryogenic oxygen. At the core of the system is a jet engine whose after burner is modified to act as an evaporator. Liquid oxygen is pumped in, vaporized and ducted forward to the air intake through a gate. The gate is designed to control the mix of ambient oxygen and cryogenic oxygen going into the engine. It is also used as a hear shield to protect the engine from reentry temperatres.

Description

    FEDERAL SPONSORSHIP—NONE BACKGROUND OF THE INVENTION
  • This invention pertains to the field of aerospace propulsion systems. Presently, the altitude to which an aircraft can ascend is limited by the lack of oxygen in the atmosphere. This invention is intended to solve the particular problem.
    • SUMMARY OF THE INVENTION
  • The object of this invention is to enable an air breathing engine to perform at much higher altitudes that are currently unattainable. This is achieved by augmenting the oxygen with an “on board” supply of cryogenic oxygen.
    • DESCRIPTION OF THE DRAWING
  • FIG. 1 is a general arrangement which shows a generic jet engine at the core of the system. The drawing illustrates the modified after burner section, now modified to vaporize liquid oxygen, which in turn is used as a coolant for the after burner sheet metal. At the opposite end, the gate is shown, deflecting the vaporized oxygen into the intake. Also shown, are the elements of a control system which link the gate aperture to the motor driving the cryogenic pump.
    • DESCRIPTION OF THE INVENTION
  • At the start the system, liquid oxygen is pumped into the evaporator which consists of a helical coil wrapped around the cylindrical after burner. The cross-section of the coil expands progressively to accommodate the expanding oxygen. The evaporator coils stop at the turbine section where it becomes a straight duct on the topside of the engine. The vaporized oxygen now passes through an opening in the top of the rectangular intake and is deflected towards the compressor section of the engine. With the gate setting illustrated in FIG. 1, ambient air is also admitted. The air/oxygen mix passes through the compressors into the combustors where fuel is sprayed in to maintain the flame front. The oxygen rich exhaust stream then enters the after burner where more fuel is added to further increase thrust. As altitude increases the gate gradually closes off the air intake, and the system continues to run on pure oxygen. Beyond the atmosphere, the exhaust stream is vectored for steering purposes

Claims (6)

1. The hybridizing of rocket and jet engine technology.
2. The adaptation of the after burner for use as an evaporator
3. the use of vaporized liquid oxygen to oxidize hydro carbon fuel in a conventional jet engine.
4. The ducts system that conveys oxygen into the engine intake.
5. The gate that controls the air/oxygen mix going into the engine and which will act as a heat shield for re-entry purposes.
6. the control system that links the intake aperture to the cryogenic pump rate and the engine fuelling rate.
US10/876,355 2004-06-25 2004-06-25 Hybrid propulsion system Expired - Fee Related US6973774B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
US10/876,355 US6973774B1 (en) 2004-06-25 2004-06-25 Hybrid propulsion system

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US10/876,355 US6973774B1 (en) 2004-06-25 2004-06-25 Hybrid propulsion system

Publications (2)

Publication Number Publication Date
US6973774B1 US6973774B1 (en) 2005-12-13
US20050284129A1 true US20050284129A1 (en) 2005-12-29

Family

ID=35452406

Family Applications (1)

Application Number Title Priority Date Filing Date
US10/876,355 Expired - Fee Related US6973774B1 (en) 2004-06-25 2004-06-25 Hybrid propulsion system

Country Status (1)

Country Link
US (1) US6973774B1 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8256203B1 (en) * 2007-01-26 2012-09-04 The University Of Alabama In Huntsville Rocket based combined cycle propulsion unit having external rocket thrusters

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9638111B2 (en) 2011-09-14 2017-05-02 Anthony R. Martinez Providing oxidation to a gas turbine engine
CN106014687A (en) * 2015-03-31 2016-10-12 黄笳唐 Aerospace jet engine and aerospace engine taking off and landing perpendicularly
CN105841193B (en) * 2016-05-18 2018-07-20 葛明龙 Two kinds of aerospace fanjets
US10513982B2 (en) 2017-02-22 2019-12-24 Textron Innovations Inc. Rotorcraft having increased altitude density ceiling

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3110153A (en) * 1950-09-05 1963-11-12 Aerojet General Co Gas generator turbojet motor
US3237400A (en) * 1957-04-05 1966-03-01 United Aircraft Corp Turborocket engine
US5025623A (en) * 1988-09-13 1991-06-25 Mitsubishi Jukogyo Kabushiki Kaisha Rocket engine
US6202404B1 (en) * 1998-10-09 2001-03-20 Mse Technology Applications, Inc. Method and apparatus for reducing the temperature of air entering a compressor of a turbojet engine by variably injecting fluid into the incoming air
US6619031B1 (en) * 2000-04-27 2003-09-16 Vladimir V. Balepin Multi-mode multi-propellant liquid rocket engine
US6644015B2 (en) * 2001-10-29 2003-11-11 Hmx, Inc. Turbojet with precompressor injected oxidizer

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3110153A (en) * 1950-09-05 1963-11-12 Aerojet General Co Gas generator turbojet motor
US3237400A (en) * 1957-04-05 1966-03-01 United Aircraft Corp Turborocket engine
US5025623A (en) * 1988-09-13 1991-06-25 Mitsubishi Jukogyo Kabushiki Kaisha Rocket engine
US6202404B1 (en) * 1998-10-09 2001-03-20 Mse Technology Applications, Inc. Method and apparatus for reducing the temperature of air entering a compressor of a turbojet engine by variably injecting fluid into the incoming air
US6619031B1 (en) * 2000-04-27 2003-09-16 Vladimir V. Balepin Multi-mode multi-propellant liquid rocket engine
US6644015B2 (en) * 2001-10-29 2003-11-11 Hmx, Inc. Turbojet with precompressor injected oxidizer

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8256203B1 (en) * 2007-01-26 2012-09-04 The University Of Alabama In Huntsville Rocket based combined cycle propulsion unit having external rocket thrusters

Also Published As

Publication number Publication date
US6973774B1 (en) 2005-12-13

Similar Documents

Publication Publication Date Title
US10012177B2 (en) Engine comprising a rocket combustion chamber and a heat exchanger
US6619031B1 (en) Multi-mode multi-propellant liquid rocket engine
US9291124B2 (en) Combined cycle integrated combustor and nozzle system
US11920543B2 (en) Rocket propulsion systems and associated methods
GB2238080A (en) Propulsion system for an aerospace vehicle
US20050284129A1 (en) Hybrid propulsion system
US6227486B1 (en) Propulsion system for earth to orbit vehicle
US6766638B1 (en) Hydrogen peroxide based propulsion system
US12031507B2 (en) Augmented aerospike nozzle, engine including the augmented aerospike nozzle, and vehicle including the engine
RU2602656C1 (en) Return carrier rocket stage, method of its operation and gas turbine engine
JP2001317406A (en) Method and apparatus for placing a satellite in low earth orbit
US20140331682A1 (en) High-speed-launch ramjet booster
US7849670B2 (en) Propulsion system with integrated rocket accelerator
US3487643A (en) Composite ramjet/rocket propulsion unit
RU2609549C1 (en) Return stage of rocket vehicle and method of its operation
RU2609664C1 (en) Return stage of rocket vehicle, method of its operation and gas turbine engine
JP3116068B2 (en) Scrum / race combined engine
Kors Combined cycle propulsion for hypersonic flight
EP4484724A1 (en) Hydrogen liquid oxygen combined cycle engine
CN101306723A (en) Process and device for changing air resistance of moving objects
JPH02301653A (en) Air liquefying cycle engine
St et al. An evaluation of two alternate propulsion concepts for Bantam-Argus-Deeply-cooled turbojet+ rocket and pulsed detonation rocket+ ramjet
JPH04153550A (en) air liquefaction engine
CN1869424A (en) Hydrogen rocker

Legal Events

Date Code Title Description
FPAY Fee payment

Year of fee payment: 4

REMI Maintenance fee reminder mailed
LAPS Lapse for failure to pay maintenance fees
STCH Information on status: patent discontinuation

Free format text: PATENT EXPIRED DUE TO NONPAYMENT OF MAINTENANCE FEES UNDER 37 CFR 1.362

FP Lapsed due to failure to pay maintenance fee

Effective date: 20131213