US2807139A - Air-jacketed combustion chambers for jet propulsion engines, gas turbines and the like - Google Patents
Air-jacketed combustion chambers for jet propulsion engines, gas turbines and the like Download PDFInfo
- Publication number
- US2807139A US2807139A US414741A US41474154A US2807139A US 2807139 A US2807139 A US 2807139A US 414741 A US414741 A US 414741A US 41474154 A US41474154 A US 41474154A US 2807139 A US2807139 A US 2807139A
- Authority
- US
- United States
- Prior art keywords
- air
- nozzles
- fuel
- gas turbines
- combustion chambers
- 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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Classifications
-
- 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
- F23R3/04—Air inlet arrangements
- F23R3/10—Air inlet arrangements for primary air
- F23R3/12—Air inlet arrangements for primary air inducing a vortex
- F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
-
- 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
- F23R3/04—Air inlet arrangements
- F23R3/045—Air inlet arrangements using pipes
Definitions
- This invention relates to the combustion chambers of jet propulsion engines, gas turbines and the like, of the kind in which the chamber is of annular form and has air jackets around its inner and outer peripheral walls, an annular arrangement of equi-spaced fuel nozzles being mounted in the entrance end of the chamber.
- the object of the invention is to provide a construction adapted to ensure uniform combustion of the fuel discharged from the nozzles.
- the invention comprises a construction in which are provided in the inner and outer walls of the combustion chamber at positions between the fuel nozzles oppositely inclined air nozzles adapted to produce a swirling ring of air around each of the fuel jets.
- Figure 1 is a sectional side elevation illustrating a portion of an annular combustion chamber having inner and outer air jackets, and provided with the invention.
- Figure 2 is a fragmentary sectional end view on the line 22 (Figure 1), Figure 2 being drawn to a larger scale than Figure 1.
- the combustion chamber is formed by inner and outer sheet metal walls a, b of substantially cylindrical shape, and around these walls are arranged inner and outer sheet metal air-jacket walls, 0, d.
- the fuel-entrance end of the combustion chamber is constructed from a plurality of contiguous segmental plates e each of which at its centre is shaped to form a truncated conical, or other concave recess, and at the centre of the recess is formed a hole adapted to carry a burner nozzle f and a means g for swirling the air which enters the chamber around the nozzle.
- the parts of each of these plates around the said recess is preferably perforated as shown.
- annular air trunk h which receives air from a blower, and within this trunk is arranged another and smaller annular trunk i.
- the latter has a narrow entrance end and is shaped to a form of gradually increasing size, its delivery end being of approximately the same size as the combustion chamber.
- the space between the two trunks serves to convey air to the air jackets, and the inner trunk serves to convey air to the air inlets around the nozzles and the said perforations in the plates e carrying the nozzles.
- each wall has associated with it four equi-spaced air nozzles, and these are so directed towards the fuel nozzles, that the air jets therefrom serve, in conjunction with the swirling air admitted to the combustion chamber around the fuel nozzle, to form a toroidal ring of swirling air around the emerging fuel jet.
- the effect of the said rings of swirling air is to produce a uniform mixture of fuel and air in the vicinity of each nozzle and so ensure the required uniformity of combustion.
Description
Sept. 24, 1957 s. R. JACKSON 2,807,139
AIR-JACKETED COMBUSTION CHAMBERS FOR JET PROPULSION ENGINES, GAS TURBINES AND THE LIKE Filed March 8, 1954' o o o o o o o o o o 0 o o o United States Patent AIR-JACKETED COMBUSTION CHAMBERS FGR JET PROPULSION ENGINES, GAS TURBINES AND THE LIKE Squire R. Jackson, Burnley, England, assignor to Joseph Lucas (Industries) Limited, Birmingham, England Application March 8, 1954, Serial No. 414,741 1 Claim. c1. 60-39.65)
This invention relates to the combustion chambers of jet propulsion engines, gas turbines and the like, of the kind in which the chamber is of annular form and has air jackets around its inner and outer peripheral walls, an annular arrangement of equi-spaced fuel nozzles being mounted in the entrance end of the chamber.
The object of the invention is to provide a construction adapted to ensure uniform combustion of the fuel discharged from the nozzles.
The invention comprises a construction in which are provided in the inner and outer walls of the combustion chamber at positions between the fuel nozzles oppositely inclined air nozzles adapted to produce a swirling ring of air around each of the fuel jets.
In the accompanying drawings:
Figure 1 is a sectional side elevation illustrating a portion of an annular combustion chamber having inner and outer air jackets, and provided with the invention.
Figure 2 is a fragmentary sectional end view on the line 22 (Figure 1), Figure 2 being drawn to a larger scale than Figure 1.
Referring to the drawings, the combustion chamber is formed by inner and outer sheet metal walls a, b of substantially cylindrical shape, and around these walls are arranged inner and outer sheet metal air-jacket walls, 0, d. The fuel-entrance end of the combustion chamber is constructed from a plurality of contiguous segmental plates e each of which at its centre is shaped to form a truncated conical, or other concave recess, and at the centre of the recess is formed a hole adapted to carry a burner nozzle f and a means g for swirling the air which enters the chamber around the nozzle. The parts of each of these plates around the said recess is preferably perforated as shown.
The ends of the jacket walls adjacent to the fuelentrance end of the combustion chamber are connected to an annular air trunk h which receives air from a blower, and within this trunk is arranged another and smaller annular trunk i. The latter has a narrow entrance end and is shaped to a form of gradually increasing size, its delivery end being of approximately the same size as the combustion chamber. The space between the two trunks serves to convey air to the air jackets, and the inner trunk serves to convey air to the air inlets around the nozzles and the said perforations in the plates e carrying the nozzles.
For the purpose of the invention, it is desired to pro- Patented Sept. 24, 1957 vduce around the jet of atomized or vaporized fuel emerging from each nozzle, a toroidal ring of air in a swirling condition, and to achieve this purpose, there is formed in the inner wall of the combustion chamber at a position corresponding to the radial centre lines between the nozzles, a pair of adjacently placed air inlets j, and at each inlet is secured within the combustion chamber a pair of short air discharge nozzles k. Similarly air inlets m are formed in the outer wall, and at each inlet is secured a nozzle 11. The adjacent nozzles in each wall are oppositely inclined to each other and are arranged to face the upstream end of the combustion chamber so as to direct radial jets of air towards the associated fuel nozzles. The arrangement is such that each fuel nozzle has associated with it four equi-spaced air nozzles, and these are so directed towards the fuel nozzles, that the air jets therefrom serve, in conjunction with the swirling air admitted to the combustion chamber around the fuel nozzle, to form a toroidal ring of swirling air around the emerging fuel jet. The effect of the said rings of swirling air is to produce a uniform mixture of fuel and air in the vicinity of each nozzle and so ensure the required uniformity of combustion.
Having thus described my invention what I claim as new and desire to secure by Letters Patent is:
The combination with an engine combustion chamber of annular form having inner and outer peripheral walls, and an entrance at one end, of an annular arrangement of equispaced fuel nozzles in said entrance, air inlets corresponding in number to and respectively surrounding said fuel nozzles, air-swirling means in said air inlets, means supporting said air inlets and fuel nozzles and shaped to provide a recess around each of said air inlets, additional air inlets at circumferentially spaced positions in said inner and outer peripheral walls adjacent to said entrance, and air nozzles leading from said additional air inlets and situated in pairs within said chamber with the nozzles of each pair inclined away from each other, the number of pairs of air nozzles leading from the inlets in the inner peripheral wall of said chamber being equal to the number of pairs of air nozzles leading from the inlets in the outer peripheral wall of said cham her, and also equal to the number of said fuel nozzles, and the inner ends of said air nozzles being arranged to direct jets of air towards the nearest fuel nozzles so that each individual fuel nozzle has directed towards. it the air jets from one nozzle of each of four adjacent pairs, whereby the air jets serve in conjunction with the swirling air entering said chamber through the first mentioned air inlets to form swirling rings of air around the individual fuel jets emerging from said fuel nozzles.
References Cited in the file of this patent UNITED STATES PATENTS 2,488,911 Hepburn et al. Nov. 22, 1949 2,526,122 Darlington Oct. 17, 1950 2,531,810 Fyfie Nov. 28, 1950 2,541,171 McGarry Feb. 13, 1951 2,607,193 Berggren Aug. 19, 1952 2,664,702 Lloyd et al Jan. 5, 1954 2,720,080 Oulianoflr' et al Oct. 11, 1955
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US414741A US2807139A (en) | 1953-01-19 | 1954-03-08 | Air-jacketed combustion chambers for jet propulsion engines, gas turbines and the like |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB1463/53A GB736823A (en) | 1953-01-19 | 1953-01-19 | Engine combustion chambers |
US414741A US2807139A (en) | 1953-01-19 | 1954-03-08 | Air-jacketed combustion chambers for jet propulsion engines, gas turbines and the like |
Publications (1)
Publication Number | Publication Date |
---|---|
US2807139A true US2807139A (en) | 1957-09-24 |
Family
ID=9722419
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US414741A Expired - Lifetime US2807139A (en) | 1953-01-19 | 1954-03-08 | Air-jacketed combustion chambers for jet propulsion engines, gas turbines and the like |
Country Status (4)
Country | Link |
---|---|
US (1) | US2807139A (en) |
DE (1) | DE961672C (en) |
FR (1) | FR1095756A (en) |
GB (1) | GB736823A (en) |
Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4301657A (en) * | 1978-05-04 | 1981-11-24 | Caterpillar Tractor Co. | Gas turbine combustion chamber |
US5465577A (en) * | 1992-12-17 | 1995-11-14 | Asea Brown Boveri Ltd. | Gas turbine combustion chamber |
EP0803681A1 (en) * | 1996-04-24 | 1997-10-29 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Optimalisation of the mixture of combustion gas in a gas turbine combustor |
US20090090110A1 (en) * | 2007-10-04 | 2009-04-09 | Honeywell International, Inc. | Faceted dome assemblies for gas turbine engine combustors |
US20100218504A1 (en) * | 2009-02-27 | 2010-09-02 | Honeywell International Inc. | Annular rich-quench-lean gas turbine combustors with plunged holes |
US20100218503A1 (en) * | 2009-02-27 | 2010-09-02 | Honeywell International Inc. | Plunged hole arrangement for annular rich-quench-lean gas turbine combustors |
Families Citing this family (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE1199541B (en) * | 1961-12-04 | 1965-08-26 | Jan Jerie Dr Ing | Propellant gas collector for the stator of gas turbines |
GB9407029D0 (en) * | 1994-04-08 | 1994-06-08 | Rolls Royce Plc | Gas turbine engine combustion apparatus |
GB2589885A (en) * | 2019-12-11 | 2021-06-16 | Rolls Royce Plc | Combustor |
Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2488911A (en) * | 1946-11-09 | 1949-11-22 | Surface Combustion Corp | Combustion apparatus for use with turbines |
US2526122A (en) * | 1944-11-28 | 1950-10-17 | Vickers Electrical Co Ltd | Combustion chambers with perforated end walls and upstream fuel injection for combustion turbines |
US2531810A (en) * | 1946-06-05 | 1950-11-28 | Kellogg M W Co | Air inlet arrangement for combustion chamber flame tubes |
US2541171A (en) * | 1947-01-25 | 1951-02-13 | Kellogg M W Co | Air inlet structure for combustion chambers |
US2607193A (en) * | 1947-10-25 | 1952-08-19 | Curtiss Wright Corp | Annular combustion chamber with multiple notched fuel nozzles |
US2664702A (en) * | 1947-08-11 | 1954-01-05 | Power Jets Res & Dev Ltd | Cooled flame tube |
US2720080A (en) * | 1952-02-01 | 1955-10-11 | Rolls Royce | Combustion equipment for gas-turbine engines with support means for supporting the flame tube from an air casing |
Family Cites Families (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB583211A (en) * | 1940-01-24 | 1946-12-12 | Anglo Saxon Petroleum Co | Improved process and apparatus for the continuous generation of gases by reaction between air and liquid or pulverulent combustible material |
GB578764A (en) * | 1942-09-08 | 1946-07-11 | Rover Co Ltd | Improvements relating to combustion chambers for internal combustion turbines |
GB595831A (en) * | 1944-03-16 | 1947-12-18 | Power Jets Ltd | Improvements relating to combustion apparatus |
US2517015A (en) * | 1945-05-16 | 1950-08-01 | Bendix Aviat Corp | Combustion chamber with shielded fuel nozzle |
US2671314A (en) * | 1950-01-26 | 1954-03-09 | Socony Vacuum Oil Co Inc | Gas turbine and method of operation therefor |
FR1025198A (en) * | 1950-09-27 | 1953-04-13 | Continuous combustion chamber and explosive waves | |
FR1052475A (en) * | 1952-03-15 | 1954-01-25 | Snecma | Combustion chambers particularly suitable for gas turbines |
-
1953
- 1953-01-19 GB GB1463/53A patent/GB736823A/en not_active Expired
-
1954
- 1954-03-08 US US414741A patent/US2807139A/en not_active Expired - Lifetime
- 1954-03-11 DE DEL18237A patent/DE961672C/en not_active Expired
- 1954-03-16 FR FR1095756D patent/FR1095756A/en not_active Expired
Patent Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2526122A (en) * | 1944-11-28 | 1950-10-17 | Vickers Electrical Co Ltd | Combustion chambers with perforated end walls and upstream fuel injection for combustion turbines |
US2531810A (en) * | 1946-06-05 | 1950-11-28 | Kellogg M W Co | Air inlet arrangement for combustion chamber flame tubes |
US2488911A (en) * | 1946-11-09 | 1949-11-22 | Surface Combustion Corp | Combustion apparatus for use with turbines |
US2541171A (en) * | 1947-01-25 | 1951-02-13 | Kellogg M W Co | Air inlet structure for combustion chambers |
US2664702A (en) * | 1947-08-11 | 1954-01-05 | Power Jets Res & Dev Ltd | Cooled flame tube |
US2607193A (en) * | 1947-10-25 | 1952-08-19 | Curtiss Wright Corp | Annular combustion chamber with multiple notched fuel nozzles |
US2720080A (en) * | 1952-02-01 | 1955-10-11 | Rolls Royce | Combustion equipment for gas-turbine engines with support means for supporting the flame tube from an air casing |
Cited By (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4301657A (en) * | 1978-05-04 | 1981-11-24 | Caterpillar Tractor Co. | Gas turbine combustion chamber |
US5465577A (en) * | 1992-12-17 | 1995-11-14 | Asea Brown Boveri Ltd. | Gas turbine combustion chamber |
EP0803681A1 (en) * | 1996-04-24 | 1997-10-29 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Optimalisation of the mixture of combustion gas in a gas turbine combustor |
FR2748088A1 (en) * | 1996-04-24 | 1997-10-31 | Snecma | OPTIMIZATION OF THE MIXTURE OF BURNED GASES IN AN ANNULAR COMBUSTION CHAMBER |
US5934067A (en) * | 1996-04-24 | 1999-08-10 | Societe National D'etude Et De Construction De Moteurs D'aviation (Snecma) | Gas turbine engine combustion chamber for optimizing the mixture of burned gases |
US20090090110A1 (en) * | 2007-10-04 | 2009-04-09 | Honeywell International, Inc. | Faceted dome assemblies for gas turbine engine combustors |
US20100218504A1 (en) * | 2009-02-27 | 2010-09-02 | Honeywell International Inc. | Annular rich-quench-lean gas turbine combustors with plunged holes |
US20100218503A1 (en) * | 2009-02-27 | 2010-09-02 | Honeywell International Inc. | Plunged hole arrangement for annular rich-quench-lean gas turbine combustors |
US8141365B2 (en) * | 2009-02-27 | 2012-03-27 | Honeywell International Inc. | Plunged hole arrangement for annular rich-quench-lean gas turbine combustors |
US8171740B2 (en) | 2009-02-27 | 2012-05-08 | Honeywell International Inc. | Annular rich-quench-lean gas turbine combustors with plunged holes |
Also Published As
Publication number | Publication date |
---|---|
FR1095756A (en) | 1955-06-06 |
GB736823A (en) | 1955-09-14 |
DE961672C (en) | 1957-04-11 |
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