GB2483643A - A cooled afterburner - Google Patents

A cooled afterburner Download PDF

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Publication number
GB2483643A
GB2483643A GB1015248.6A GB201015248A GB2483643A GB 2483643 A GB2483643 A GB 2483643A GB 201015248 A GB201015248 A GB 201015248A GB 2483643 A GB2483643 A GB 2483643A
Authority
GB
United Kingdom
Prior art keywords
afterburner
air
vanes
conical guide
angle
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Withdrawn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
GB1015248.6A
Other versions
GB201015248D0 (en
Inventor
Stephen Desmond Lewis
Sarah El Moussa
Georgios Doulgeris
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 GB1015248.6A priority Critical patent/GB2483643A/en
Publication of GB201015248D0 publication Critical patent/GB201015248D0/en
Publication of GB2483643A publication Critical patent/GB2483643A/en
Withdrawn legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/46—Nozzles having means for adding air to the jet or for augmenting the mixing region between the jet and the ambient air, e.g. for silencing
    • 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
    • F02K3/08—Plants including a gas turbine driving a compressor or a ducted fan with supplementary heating of the working fluid; Control thereof
    • F02K3/10—Plants including a gas turbine driving a compressor or a ducted fan with supplementary heating of the working fluid; Control thereof by after-burners
    • 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
    • F02K7/14—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 with external combustion, e.g. scram-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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
    • F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2240/00—Components
    • F05B2240/10—Stators
    • F05B2240/13—Stators to collect or cause flow towards or away from turbines
    • F05B2240/132—Stators to collect or cause flow towards or away from turbines creating a vortex or tornado effect
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/127—Vortex generators, turbulators, or the like, for mixing
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/128—Nozzles
    • 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/23—Three-dimensional prismatic
    • F05D2250/232—Three-dimensional prismatic conical

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

An afterburner 2 with a bypass air flow 4 wherein the afterburner comprises a conical guide or vane 1 which is used to spin air which enters from around the outside of the afterburner. The spun air forms an insulating jacket 6 around the combustion 7 of the fuel in the afterburner. The conical guide or vanes may be movable such that the angle between the afterburner and the bypass air flow may be variable thus altering the amount of air which is received into an engine for different speeds. The angle of the spun air may be between 0 degrees and 45 degrees. The conical guide or vanes may be movable with hydraulics.

Description

The Cooled Afterburner This invention relates to an afterburner of a jet engine which is resistant to overheating and melting with prolonged use.
When afterburners are used the already hot exhaust becomes even hotter due to the addition and burning of the afterburners fuel. Hence the afterburner cannot be deployed for as long or has a shortened service life. To overcome this, the present invention proposes an afterburner with a bypassed air intake consisting of a conical guide and/or vanes which is used to spin air which enters from around the outside of the afterburner from the forward motion of the engine into the afterburner to contain the combustion of the fuel, forming an insulating jacket around the combustion of the fuel in the afterburner.
The conical guide and vanes that spin the air will make an air jacket that contains the combustion of the fuel that will make sure that combustion of the fuel will not come into contact with the walls of the afterburner, reducing the risk of the afterburner duct walls melting and giving a longer service life. The centrifugal force that the spun air exerts will ensure that the air will cling to the inner afterburner casing.
Preferably, the conical guide and/or vanes are movable to vary the angle between the afterburner and the bypassed air flow to allow different amounts of air into the engine for different speeds.
Preferably, the angle of the spun air will be variable between 0 and 45 degrees by moving the conical guide and/or vanes.
Preferably, the conical guide and/or vanes are movable with hydraulics.
An example of the invention will now be described by referring to the accompanying drawings: -figure 1 shows a cutaway end view of the cooled afterburner without a turbojet/turbofan engine in operation according to the invention.
-figure 2 shows a side view of the cooled afterburner in operation according to the invention.
A conical guide with vanes 1 is attached to an afterburner 2 of a turbojet/turbofan engine 3 at an angle near the rear of the engine. This conical guide with vanes may be moved to vary the angle between the afterburner and the bypassed air flow 4 with hydraulics, to vary the amount of air entering the afterburner for different speeds. When the engine is moving through the atmosphere 5 the conical guide and vanes spin the air 6 and the centrifugal force ensures the air clings to the inner afterburner casing. The angle of the spun air may be variable between 0 and 45 degrees by moving the conical guide and/or vanes with hydraulics. Combustion 7 then takes place inside the spinning air without coming into contact with the inner engine casing in the afterburners combustion chamber.

Claims (4)

  1. Claims 1 An afterburner with a bypassed air intake consisting of a conical guide and/or vanes which is used to spin air which enters from around the outside of the afterburner from the forward motion of the engine into the afterburner to contain the combustion of the fuel, forming an insulating jacket around the combustion of the fuel in the afterburner.
  2. 2 An afterburner with a bypassed air intake according to claim 1, in which the conical guide and/or vanes are movable to vary the angle between the afterburner and the bypassed air flow to allow different amounts of air into the engine for different speeds.
  3. 3 An afterburner with a bypassed air intake according to claim 2, in which the angle of the spun air will be variable between 0 and 45 degrees by moving the conical guide and/or vanes.
  4. 4 An afterburner with a bypassed air intake acccrding to any of the preceding claims in which the conical guide and/or vanes are movable with hydraulics.
GB1015248.6A 2010-09-14 2010-09-14 A cooled afterburner Withdrawn GB2483643A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB1015248.6A GB2483643A (en) 2010-09-14 2010-09-14 A cooled afterburner

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB1015248.6A GB2483643A (en) 2010-09-14 2010-09-14 A cooled afterburner

Publications (2)

Publication Number Publication Date
GB201015248D0 GB201015248D0 (en) 2010-10-27
GB2483643A true GB2483643A (en) 2012-03-21

Family

ID=43065111

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1015248.6A Withdrawn GB2483643A (en) 2010-09-14 2010-09-14 A cooled afterburner

Country Status (1)

Country Link
GB (1) GB2483643A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2535811A (en) * 2015-02-28 2016-08-31 Desmond Lewis Stephen Pre-cooling for aerospace engines

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112228905B (en) * 2020-10-13 2022-01-21 西北工业大学 Channel structure capable of restraining flow distribution deviation of supercritical fluid

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1118569A (en) * 1964-10-20 1968-07-03 Felix Berner Mechanical energy exchange between two fluid media
US3830431A (en) * 1973-03-23 1974-08-20 Nasa Abating exhaust noises in jet engines
JPH08312462A (en) * 1995-05-16 1996-11-26 Ishikawajima Harima Heavy Ind Co Ltd Bypass channel variable nozzle for supersonic aircraft
EP1445465A1 (en) * 2003-02-06 2004-08-11 The Boeing Company Combination of core engine with ramjet engine incorporating swirl augmented combustion
GB2432887A (en) * 2005-11-29 2007-06-06 Stephen Desmond Lewis An air intake of a ramjet

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1118569A (en) * 1964-10-20 1968-07-03 Felix Berner Mechanical energy exchange between two fluid media
US3830431A (en) * 1973-03-23 1974-08-20 Nasa Abating exhaust noises in jet engines
JPH08312462A (en) * 1995-05-16 1996-11-26 Ishikawajima Harima Heavy Ind Co Ltd Bypass channel variable nozzle for supersonic aircraft
EP1445465A1 (en) * 2003-02-06 2004-08-11 The Boeing Company Combination of core engine with ramjet engine incorporating swirl augmented combustion
GB2432887A (en) * 2005-11-29 2007-06-06 Stephen Desmond Lewis An air intake of a ramjet

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2535811A (en) * 2015-02-28 2016-08-31 Desmond Lewis Stephen Pre-cooling for aerospace engines
GB2535811B (en) * 2015-02-28 2018-07-11 Desmond Lewis Stephen Pre-cooling for aerospace engines

Also Published As

Publication number Publication date
GB201015248D0 (en) 2010-10-27

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Legal Events

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