WO2005008043A2 - Tangentially exhausting revolving combustion chamber in a revolving ramjet, turbojet, turbofan, gas turbine or other jet engine - Google Patents

Tangentially exhausting revolving combustion chamber in a revolving ramjet, turbojet, turbofan, gas turbine or other jet engine Download PDF

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Publication number
WO2005008043A2
WO2005008043A2 PCT/ZA2004/000083 ZA2004000083W WO2005008043A2 WO 2005008043 A2 WO2005008043 A2 WO 2005008043A2 ZA 2004000083 W ZA2004000083 W ZA 2004000083W WO 2005008043 A2 WO2005008043 A2 WO 2005008043A2
Authority
WO
WIPO (PCT)
Prior art keywords
revolving
combustion chamber
ramjet
turbofan
engine
Prior art date
Application number
PCT/ZA2004/000083
Other languages
French (fr)
Other versions
WO2005008043A3 (en
Inventor
Eugene Thomas David Archery
Original Assignee
Eugene Thomas David Archery
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 Eugene Thomas David Archery filed Critical Eugene Thomas David Archery
Publication of WO2005008043A2 publication Critical patent/WO2005008043A2/en
Publication of WO2005008043A3 publication Critical patent/WO2005008043A3/en

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
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/14—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
    • F02C3/16—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant the combustion chambers being formed at least partly in the turbine rotor or in an other rotating part of the plant
    • 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
    • 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
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/56—Combustion chambers having rotary flame tubes

Definitions

  • This invention relates to a tangentially exhausting revolving combustion chamber in a revolving ramjet engine, a turbojet engine, a turbofan engine, a gas turbine engine or other jet engine.
  • Ramjet combustion chambers have been used to power a helicopter rotor. These ramjets were fixed to the tips of the rotor blades.
  • This invention consists of a combustion chamber or chambers, which rotate around an axis and exhaust/s tangentially to its/their circle of rotation within a jet engine.
  • the combustion chamber/s may be fitted in an otherwise conventional turbojet, turbofan or gas turbine engine and linked to drive the air compressors and/or other devices.
  • the combustion chamber/s may be integrated with supersonic speed ram charging air scoops, which feed inlet air into the combustion chamber/s, forming (a) revolving ramjet(s). In this form there may or may not be prior air compressor stages.
  • Figure 1 is a schematic cross sectional rear view of multiple combustion chambers. Items 1 are the combustion chambers. Item 2 is the engine casing. Items 3 are the tangential exhausts and item 4 is the axis of rotation. 2.
  • Figure2 is a schematic side view of a single annular combustion chamber with wholly tangential exhausts. Item 1 is the exhaust. Item 2 is the axis of rotation. 3.
  • Figure 3 is a schematic side view of a single annular combustion chamber with partly tangential and partly rearward exhausts. Item 1 is the exhaust. Item 2 is the axis of rotation.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

This invention consists of a combustion chamber or chambers (1), which around an axis (4) and exhaust/s tangentially (3) to its/their circle of rotation within a jet engine (2). The combustion chamber/s may be fitted in an otherwise conventional turbojet, turbofan or gas turbine engine and linked to drive the air compressors and/or other devices. The combustion chamber/s (1) may be integrated with supersonic speed ram charging air scoops, which feed inlet air into the combustion chamber/s, forming (a) revolving ramjet(s). In this form, there may or may not be prior air compressor stages.

Description

Tangential ly exhausting revolving combustion chamber in a revolving ramjet turbojet turbofan. gas turbine or other jet engine-
Technical Field
This invention relates to a tangentially exhausting revolving combustion chamber in a revolving ramjet engine, a turbojet engine, a turbofan engine, a gas turbine engine or other jet engine.
Background Art
Ramjet combustion chambers have been used to power a helicopter rotor. These ramjets were fixed to the tips of the rotor blades.
It is the object of this invention to use a revolving combustion chamber or chambers within a jet engine casing to generate torque to drive the ramjet, air compressor/s and#/or other devices.
Disclosure of the invention.
This invention consists of a combustion chamber or chambers, which rotate around an axis and exhaust/s tangentially to its/their circle of rotation within a jet engine.
The combustion chamber/s may be fitted in an otherwise conventional turbojet, turbofan or gas turbine engine and linked to drive the air compressors and/or other devices.
The combustion chamber/s may be integrated with supersonic speed ram charging air scoops, which feed inlet air into the combustion chamber/s, forming (a) revolving ramjet(s). In this form there may or may not be prior air compressor stages.
It will be appreciated that many modifications and/or improvements of the invention are possible without departing from the spirit or scope of the invention. Brief description of drawings.
1. Figure 1 is a schematic cross sectional rear view of multiple combustion chambers. Items 1 are the combustion chambers. Item 2 is the engine casing. Items 3 are the tangential exhausts and item 4 is the axis of rotation. 2. Figure2 is a schematic side view of a single annular combustion chamber with wholly tangential exhausts. Item 1 is the exhaust. Item 2 is the axis of rotation. 3. Figure 3 is a schematic side view of a single annular combustion chamber with partly tangential and partly rearward exhausts. Item 1 is the exhaust. Item 2 is the axis of rotation.

Claims

Claims
1. A revolving combustion chamber/s within a revolving ramjet engine, turbojet engine, turbofan engine, gas turbine engine or other jet engine.
2. A revolving combustion chamber/s within an otherwise conventional turbojet, turbofan or gas turbine engine linked to drive the air compressors and/or other devices.
3. A revolving combustion chamber/s, within a revolving ramjet engine, integrated with supersonic speed ram charging air scoops, which feed inlet air into the combustion chamber/s, forming (a) revolving ramjet(s).
4. A revolving combustion chamber(s) substantially as described with reference to the accompanying drawings.
PCT/ZA2004/000083 2003-07-23 2004-07-23 Tangentially exhausting revolving combustion chamber in a revolving ramjet, turbojet, turbofan, gas turbine or other jet engine WO2005008043A2 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
ZA03/5809 2003-07-23
ZA200305809 2003-07-23

Publications (2)

Publication Number Publication Date
WO2005008043A2 true WO2005008043A2 (en) 2005-01-27
WO2005008043A3 WO2005008043A3 (en) 2005-02-24

Family

ID=34081014

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/ZA2004/000083 WO2005008043A2 (en) 2003-07-23 2004-07-23 Tangentially exhausting revolving combustion chamber in a revolving ramjet, turbojet, turbofan, gas turbine or other jet engine

Country Status (1)

Country Link
WO (1) WO2005008043A2 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10539073B2 (en) 2017-03-20 2020-01-21 Chester L Richards, Jr. Centrifugal gas compressor

Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US560196A (en) * 1896-05-19 Pneumatic tire
GB727796A (en) * 1951-05-10 1955-04-06 Nat Res Dev Improvements relating to combustion equipment for burning liquid fuel and to gas turbine plant in which it is incorporated
US2709889A (en) * 1951-06-22 1955-06-07 Wadsworth W Mount Gas turbine using revolving ram jet burners
GB2019943A (en) * 1978-04-29 1979-11-07 Stidworthy F M Gas turbine engine
GB2189844A (en) * 1986-04-30 1987-11-04 Rolls Royce Gas turbine engines
US5372005A (en) * 1992-09-14 1994-12-13 Lawler; Shawn P. Method and apparatus for power generation
US5660038A (en) * 1992-01-24 1997-08-26 Stone; Joseph Walter Rotary jet engine
US6434924B1 (en) * 1996-12-16 2002-08-20 Ramgen Power Systems, Inc. Ramjet engine for power generation
EP1455065A2 (en) * 2003-03-06 2004-09-08 General Electric Company Pulse detonation system for a gas turbine engine
US20040194469A1 (en) * 2003-04-02 2004-10-07 Lawrence Butler Pulse detonation system for a gas turbine engine

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US560196A (en) * 1896-05-19 Pneumatic tire
GB727796A (en) * 1951-05-10 1955-04-06 Nat Res Dev Improvements relating to combustion equipment for burning liquid fuel and to gas turbine plant in which it is incorporated
US2709889A (en) * 1951-06-22 1955-06-07 Wadsworth W Mount Gas turbine using revolving ram jet burners
GB2019943A (en) * 1978-04-29 1979-11-07 Stidworthy F M Gas turbine engine
GB2189844A (en) * 1986-04-30 1987-11-04 Rolls Royce Gas turbine engines
US5660038A (en) * 1992-01-24 1997-08-26 Stone; Joseph Walter Rotary jet engine
US5372005A (en) * 1992-09-14 1994-12-13 Lawler; Shawn P. Method and apparatus for power generation
US6434924B1 (en) * 1996-12-16 2002-08-20 Ramgen Power Systems, Inc. Ramjet engine for power generation
EP1455065A2 (en) * 2003-03-06 2004-09-08 General Electric Company Pulse detonation system for a gas turbine engine
US20040194469A1 (en) * 2003-04-02 2004-10-07 Lawrence Butler Pulse detonation system for a gas turbine engine

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10539073B2 (en) 2017-03-20 2020-01-21 Chester L Richards, Jr. Centrifugal gas compressor

Also Published As

Publication number Publication date
WO2005008043A3 (en) 2005-02-24

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