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
Links
Images
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.
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 (fr) |
DE (1) | DE961672C (fr) |
FR (1) | FR1095756A (fr) |
GB (1) | GB736823A (fr) |
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 (fr) * | 1996-04-24 | 1997-10-29 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Optimisation du mélange des gaz brûlés dans une chambre de combustion annulaire |
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 |
---|---|---|---|---|
GB980363A (en) * | 1961-12-04 | 1965-01-13 | Jan Jerie | Improvements in or relating to 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 (fr) * | 1950-09-27 | 1953-04-13 | Chambre à combustion continue et ondes explosives | |
FR1052475A (fr) * | 1952-03-15 | 1954-01-25 | Snecma | Chambres de combustion convenant en particulier aux turbines à gaz |
-
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/de not_active Expired
- 1954-03-16 FR FR1095756D patent/FR1095756A/fr 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 (fr) * | 1996-04-24 | 1997-10-29 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Optimisation du mélange des gaz brûlés dans une chambre de combustion annulaire |
FR2748088A1 (fr) * | 1996-04-24 | 1997-10-31 | Snecma | Optimisation du melange de gaz brules dans une chambre de combustion annulaire |
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 |
---|---|
DE961672C (de) | 1957-04-11 |
GB736823A (en) | 1955-09-14 |
FR1095756A (fr) | 1955-06-06 |
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