US3921391A - Combustor wing vortex generators - Google Patents
Combustor wing vortex generators Download PDFInfo
- Publication number
- US3921391A US3921391A US243720A US24372072A US3921391A US 3921391 A US3921391 A US 3921391A US 243720 A US243720 A US 243720A US 24372072 A US24372072 A US 24372072A US 3921391 A US3921391 A US 3921391A
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- US
- United States
- Prior art keywords
- chamber
- wings
- combustor
- flameholder
- airflow
- 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 - Lifetime
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-
- 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
Definitions
- ABSTRACT A combustor of a ramjet engine having a plurality of wings of aerofoil cross-section extending inwardly from the combustor wall at the air inlet and in advance of the pilot flame.
- the wings are of finite aspect References Cited ratio and are pitched to an angle of attack to generate UNITED STATES PATENTS a vortex downstream of the pilot flame.
- a flameholder in a ramjet combustor generally has two basic components, namely a sheltered region where a small amount of a fuel is mixed with a small amount of air to yield a small flame or pilot and a device for spreading the flame to the remainder of the fuel air mixture effecting complete combustion of the fuel.
- a gutter is commonly used to accomplish this.
- a gutter provides a sheltered region for the flame to spread from the pilot. Mixing of the burned gases with the unburned fuel-air mixture then occurs in the gutter wake. This allows combustion of the remaining fuel-air mixture.
- a gutter does not actively mix the burned and unburned gases, but merely provides a large flameholding region. Of course some turbulence is introduced due to the wakes caused by the gutters. A large number of gutters (on the order of six) is required to spread the flame to all of the fuel-air mixture within a reasonable length of the combustor. This causes an increase in drag with a resultant loss in total pressure which decreases the performance of the combustor. Because the gutters are in Contact with the flame they must be fabricated from high temperature materials and coated to survive the thermal environment.
- a more advantageous method of affecting a fuel-air mixture employs wing vortex generators as shown in the patent to Lee US. Pat. No. 2,607,191 dated Aug. 19, 1952. There are several advantages to the wing vortex generator concept:
- the action of the vortex is very effective in mixing the burned and unburned gases and can therefore allow the use of very short combustion chambers which still operate at high efficiency. This allows a significant saving in ramjet weight and volume.
- the wing vortex generators need be at only a small angle of attack to accomplish efficient mixing and therefore have low drag. They are simple to fabricate. Because they are located upstream of the pilot flame and thus do not touch the flame, they can be fabricated from conventional, nonthermal-coated materials and are therefore inexpensive.
- the vortex generators are small wings of finite aspect ratio as opposed to turning vanes, which would span the duct thus having infinite aspect ratio. Turning vanes, also, cause an overall swirl of the flow. Vortex generators could easily be mechanized to vary the angle of attack during flight so that maximum mixing would be accomplished only during those periods of flight when efficient combustion is difficult to achieve, e.g., high altitude.
- a combustor of a ramjet engine having a plurality of wings of aerofoil cross-section extending inwardly from the combustor wall or outwardly from a fuel injector or the like at the air inlet end and upstream of the pilot flame.
- the wings are of finite aspect ratio and are pitched to an angle of attack to generate a vortex downstream of the pilot flame.
- FIGURE shows an elevation view of the invention with a portion of the combustor wall cut away.
- Wing vortex generators l in the configuration of an aerofoil and extending from cumbustor wall 2 create trailing vortices 3. Whenever a wing of finite aspect ratio is pitched to an angle of attack it generates a trailing vortex because of the pressure difference between the bottom and top of the wing. This vortex causes rapid mixing of the burned and unburned gases resulting in flamespreading.
- Vortices 3 extend past flameholder 4 and into the flame front created by the flameholder.
- a vortex generator in a combustor for a ramjet type engine comprising:
- a hollow cylindrical chamber of substantial wall thickness having an opening completely across its inner diameter for allowing airflow in an axial direction through said chamber;
- flameholder means positioned within said chamber a substantial distance from said opening for creating said flame front
- each of said wings projecting from said chamber wall at right angles to the longitudinal axis of said chamber with the free ends of each of said wings extending to a position adjacent each other near the center of said chamber and having the cordwise dimension of each of said wings slanted with respect to axial airflow through said chamber;
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
Abstract
A combustor of a ramjet engine having a plurality of wings of aerofoil cross-section extending inwardly from the combustor wall at the air inlet and in advance of the pilot flame. The wings are of finite aspect ratio and are pitched to an angle of attack to generate a vortex downstream of the pilot flame.
Description
[ Nov. 25, 1975 United States Patent [1 1 Hall et a1.
X P 2 9 3 O 6 Blackman et al.. Sloan d r m A m m T D v m G n m H w M Sr. RRM O 0 P T. SA& Rm BEt MNw OE CGm M Q 5 U both of China Lake, Calif.
228,976 5/1959 Austra1ia............................60/39.72
[73] Assignee: The United States of America as represented by the Secretary of the Navy, Washington, DC.
Apr. 13, 1972 Primary ExaminerCar1t0n R. Croyle Assistant ExaminerRobert E. Garrett [22] Filed:
Attorney, Agent, or Firm-R. S. Sciascia; Roy Miller; Robert F. Beers [21] Appl. No.: 243,720
[57] ABSTRACT A combustor of a ramjet engine having a plurality of wings of aerofoil cross-section extending inwardly from the combustor wall at the air inlet and in advance of the pilot flame. The wings are of finite aspect References Cited ratio and are pitched to an angle of attack to generate UNITED STATES PATENTS a vortex downstream of the pilot flame.
2,558,816 Bruynes......................... 60/39.72 R 1 Claim, 1 Drawing Figure l//////Ff///////////////////// US. Patent Nov. 25, 1975 3,921,391
COMBUSTOR WING VORTEX GENERATORS BACKGROUND OF THE INVENTION A flameholder in a ramjet combustor generally has two basic components, namely a sheltered region where a small amount of a fuel is mixed with a small amount of air to yield a small flame or pilot and a device for spreading the flame to the remainder of the fuel air mixture effecting complete combustion of the fuel. A gutter is commonly used to accomplish this.
A gutter provides a sheltered region for the flame to spread from the pilot. Mixing of the burned gases with the unburned fuel-air mixture then occurs in the gutter wake. This allows combustion of the remaining fuel-air mixture.
A gutter does not actively mix the burned and unburned gases, but merely provides a large flameholding region. Of course some turbulence is introduced due to the wakes caused by the gutters. A large number of gutters (on the order of six) is required to spread the flame to all of the fuel-air mixture within a reasonable length of the combustor. This causes an increase in drag with a resultant loss in total pressure which decreases the performance of the combustor. Because the gutters are in Contact with the flame they must be fabricated from high temperature materials and coated to survive the thermal environment.
A more advantageous method of affecting a fuel-air mixture employs wing vortex generators as shown in the patent to Lee US. Pat. No. 2,607,191 dated Aug. 19, 1952. There are several advantages to the wing vortex generator concept:
The action of the vortex is very effective in mixing the burned and unburned gases and can therefore allow the use of very short combustion chambers which still operate at high efficiency. This allows a significant saving in ramjet weight and volume. The wing vortex generators need be at only a small angle of attack to accomplish efficient mixing and therefore have low drag. They are simple to fabricate. Because they are located upstream of the pilot flame and thus do not touch the flame, they can be fabricated from conventional, nonthermal-coated materials and are therefore inexpensive. The vortex generators are small wings of finite aspect ratio as opposed to turning vanes, which would span the duct thus having infinite aspect ratio. Turning vanes, also, cause an overall swirl of the flow. Vortex generators could easily be mechanized to vary the angle of attack during flight so that maximum mixing would be accomplished only during those periods of flight when efficient combustion is difficult to achieve, e.g., high altitude.
SUMMARY OF THE INVENTION A combustor of a ramjet engine having a plurality of wings of aerofoil cross-section extending inwardly from the combustor wall or outwardly from a fuel injector or the like at the air inlet end and upstream of the pilot flame. The wings are of finite aspect ratio and are pitched to an angle of attack to generate a vortex downstream of the pilot flame.
BRIEF DESCRIPTION OF THE DRAWING The FIGURE shows an elevation view of the invention with a portion of the combustor wall cut away.
DESCRIPTION OF THE PREFERRED EMBODIMENT Wing vortex generators l in the configuration of an aerofoil and extending from cumbustor wall 2 create trailing vortices 3. Whenever a wing of finite aspect ratio is pitched to an angle of attack it generates a trailing vortex because of the pressure difference between the bottom and top of the wing. This vortex causes rapid mixing of the burned and unburned gases resulting in flamespreading.
What is claimed is:
l. A vortex generator in a combustor for a ramjet type engine comprising:
a hollow cylindrical chamber of substantial wall thickness having an opening completely across its inner diameter for allowing airflow in an axial direction through said chamber;
a flame front;
flameholder means positioned within said chamber a substantial distance from said opening for creating said flame front;
a plurality of spaced solid wings of airfoil cross section positioned upstream of said flameholder, each of said wings projecting from said chamber wall at right angles to the longitudinal axis of said chamber with the free ends of each of said wings extending to a position adjacent each other near the center of said chamber and having the cordwise dimension of each of said wings slanted with respect to axial airflow through said chamber;
whereby airflow through said chamber is caused to eddy downstream of the trailing edges of the wings to actively and rapidly mix the air with the area of
Claims (1)
1. A vortex generator in a combustor for a ramjet type engine comprising: a hollow cylindrical chamber of substantial wall thickness having an opening completely across its inner diameter for allowing airflow in an axial direction through said chamber; a flame front; flameholder means positioned within said chamber a substantial distance from said opening for creating said flame front; a plurality of spaced solid wings of airfoil cross section positioned upstream of said flameholder, each of said wings projecting from said chamber wall at right angles to the longitudinal axis of said chamber with the free ends of each of said wings extending to a position adjacent each other near the center of said chamber and having the cordwise dimension of each of said wings slanted with respect to axial airflow through said chamber; whereby airflow through said chamber is caused to eddy downstream of the trailing edges of the wings to actively and rapidly mix the air with the area of said flameholder.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US243720A US3921391A (en) | 1972-04-13 | 1972-04-13 | Combustor wing vortex generators |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US243720A US3921391A (en) | 1972-04-13 | 1972-04-13 | Combustor wing vortex generators |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| US3921391A true US3921391A (en) | 1975-11-25 |
Family
ID=22919853
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| US243720A Expired - Lifetime US3921391A (en) | 1972-04-13 | 1972-04-13 | Combustor wing vortex generators |
Country Status (1)
| Country | Link |
|---|---|
| US (1) | US3921391A (en) |
Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4076454A (en) * | 1976-06-25 | 1978-02-28 | The United States Of America As Represented By The Secretary Of The Air Force | Vortex generators in axial flow compressor |
| US4445339A (en) * | 1980-11-24 | 1984-05-01 | General Electric Co. | Wingtip vortex flame stabilizer for gas turbine combustor flame holder |
| US5323614A (en) * | 1992-01-13 | 1994-06-28 | Hitachi, Ltd. | Combustor for gas turbine |
| US6575733B1 (en) * | 1997-11-10 | 2003-06-10 | Gourmeli International N.V. | Fuel combustion method and reactor |
| US20030152878A1 (en) * | 1997-11-10 | 2003-08-14 | Staffler Franz Josef | Streamlined body and combustion apparatus |
| US20050026096A1 (en) * | 2001-11-23 | 2005-02-03 | Staffler Franz Josef | Streamlined body and combustion apparatus having such a streamlined body |
| CN1318748C (en) * | 2003-10-31 | 2007-05-30 | 王德强 | Super combustion pressed engine |
| CN101956632A (en) * | 2010-10-21 | 2011-01-26 | 西北工业大学 | Air suction engine combustion chamber with turbulent flow post |
| CN102278232A (en) * | 2011-05-26 | 2011-12-14 | 南京航空航天大学 | Modified scramjet combustion chamber and design method of swirler thereof |
| CN107620653A (en) * | 2017-09-27 | 2018-01-23 | 西北工业大学 | A kind of disturbing flow device for solid-rocket combustion gas scramjet engine |
| US20180100433A1 (en) * | 2016-10-07 | 2018-04-12 | General Electric Company | Component assembly for a gas turbine engine |
| RU2734965C1 (en) * | 2019-04-29 | 2020-10-26 | Николай Иванович Возисов | Method of launching payload into orbit and reusable cr ejector stage for its implementation |
| US20230296119A1 (en) * | 2020-07-23 | 2023-09-21 | Bae Systems Plc | Arrangements, duct arrangements and methods |
| US12103664B2 (en) | 2020-07-23 | 2024-10-01 | Bae Systems Plc | Arrangement for influencing liquid flow and a method |
| US12258120B2 (en) | 2020-07-23 | 2025-03-25 | Bae Systems Plc | Arrangement for influencing liquid flow and a method |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2558816A (en) * | 1947-08-16 | 1951-07-03 | United Aircraft Corp | Fluid mixing device |
| US2607191A (en) * | 1947-11-28 | 1952-08-19 | United Aircraft Corp | Vortex producing mechanism for mixing combustion chamber fluids |
| US2844001A (en) * | 1953-01-06 | 1958-07-22 | Gen Electric | Flow straightening vanes for diffuser passages |
| US2930195A (en) * | 1956-02-14 | 1960-03-29 | United Aircraft Corp | Oscillating flow combustion chamber |
| US2981065A (en) * | 1951-01-26 | 1961-04-25 | David H Sloan | Ramjet device |
-
1972
- 1972-04-13 US US243720A patent/US3921391A/en not_active Expired - Lifetime
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2558816A (en) * | 1947-08-16 | 1951-07-03 | United Aircraft Corp | Fluid mixing device |
| US2607191A (en) * | 1947-11-28 | 1952-08-19 | United Aircraft Corp | Vortex producing mechanism for mixing combustion chamber fluids |
| US2981065A (en) * | 1951-01-26 | 1961-04-25 | David H Sloan | Ramjet device |
| US2844001A (en) * | 1953-01-06 | 1958-07-22 | Gen Electric | Flow straightening vanes for diffuser passages |
| US2930195A (en) * | 1956-02-14 | 1960-03-29 | United Aircraft Corp | Oscillating flow combustion chamber |
Cited By (20)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4076454A (en) * | 1976-06-25 | 1978-02-28 | The United States Of America As Represented By The Secretary Of The Air Force | Vortex generators in axial flow compressor |
| US4445339A (en) * | 1980-11-24 | 1984-05-01 | General Electric Co. | Wingtip vortex flame stabilizer for gas turbine combustor flame holder |
| US5323614A (en) * | 1992-01-13 | 1994-06-28 | Hitachi, Ltd. | Combustor for gas turbine |
| US6575733B1 (en) * | 1997-11-10 | 2003-06-10 | Gourmeli International N.V. | Fuel combustion method and reactor |
| US20030152878A1 (en) * | 1997-11-10 | 2003-08-14 | Staffler Franz Josef | Streamlined body and combustion apparatus |
| US8979525B2 (en) | 1997-11-10 | 2015-03-17 | Brambel Trading Internacional LDS | Streamlined body and combustion apparatus |
| US20050026096A1 (en) * | 2001-11-23 | 2005-02-03 | Staffler Franz Josef | Streamlined body and combustion apparatus having such a streamlined body |
| CN1318748C (en) * | 2003-10-31 | 2007-05-30 | 王德强 | Super combustion pressed engine |
| CN101956632A (en) * | 2010-10-21 | 2011-01-26 | 西北工业大学 | Air suction engine combustion chamber with turbulent flow post |
| CN101956632B (en) * | 2010-10-21 | 2013-04-03 | 西北工业大学 | Air suction engine combustion chamber with turbulent flow post |
| CN102278232B (en) * | 2011-05-26 | 2014-05-28 | 南京航空航天大学 | Modified scramjet combustion chamber and design method of swirler thereof |
| CN102278232A (en) * | 2011-05-26 | 2011-12-14 | 南京航空航天大学 | Modified scramjet combustion chamber and design method of swirler thereof |
| US20180100433A1 (en) * | 2016-10-07 | 2018-04-12 | General Electric Company | Component assembly for a gas turbine engine |
| US11067277B2 (en) * | 2016-10-07 | 2021-07-20 | General Electric Company | Component assembly for a gas turbine engine |
| CN107620653A (en) * | 2017-09-27 | 2018-01-23 | 西北工业大学 | A kind of disturbing flow device for solid-rocket combustion gas scramjet engine |
| RU2734965C1 (en) * | 2019-04-29 | 2020-10-26 | Николай Иванович Возисов | Method of launching payload into orbit and reusable cr ejector stage for its implementation |
| US20230296119A1 (en) * | 2020-07-23 | 2023-09-21 | Bae Systems Plc | Arrangements, duct arrangements and methods |
| US12078194B2 (en) * | 2020-07-23 | 2024-09-03 | Bae Systems Plc | Arrangements, duct arrangements and methods |
| US12103664B2 (en) | 2020-07-23 | 2024-10-01 | Bae Systems Plc | Arrangement for influencing liquid flow and a method |
| US12258120B2 (en) | 2020-07-23 | 2025-03-25 | Bae Systems Plc | Arrangement for influencing liquid flow and a method |
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