US3460345A - Combustion apparatus for gas turbine engines - Google Patents
Combustion apparatus for gas turbine engines Download PDFInfo
- Publication number
- US3460345A US3460345A US694234A US3460345DA US3460345A US 3460345 A US3460345 A US 3460345A US 694234 A US694234 A US 694234A US 3460345D A US3460345D A US 3460345DA US 3460345 A US3460345 A US 3460345A
- Authority
- US
- United States
- Prior art keywords
- flame tube
- combustion
- gas turbine
- air
- ducts
- 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
-
- 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
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/34—Feeding into different combustion zones
Definitions
- This invention has for its object to provide combustion apparatus for gas turbine engines, in a convenient form.
- combustion apparatus for a gas turbine engine comprising an annular air jacket having inner and outer walls terminating at positions to define an inlet and an outlet, an annular flame tube having inner and outer walls spaced from those of the air jacket respectively, said flame tube walls defining an outlet at the downstream end, a shield within the flame tube extending substantially obliquely across it from a position near the downstream end to the upstream end, it being connected to the inner wall of the flame tube to define therewith a combustion zone, a plurality of spaced ducts communicating with the interior of the flame tube at the upstream end and extending within the outer wall of the flame tube towards the outlet, there being defined between adjacent ones of these ducts a plurality of passages communicating with the air jacket inlet whereby dilution air can enter the flame tube to mix with products of combustion leaving the combustion zone through the ducts, and there being a plurality of vanes extending across the combustion zone through openings in which fuel and air for combustion can enter the combustion zone.
- FIGURE 1 is a lengthwise cross sectional view of combustion apparatus constructed in accordance with the invention and FIGURE 2 is a transverse cross sectional view on the line II--II in FIG- URE 1.
- combustion apparatus for a gas turbine engine comprising an annular air jacket having inner and outer walls 10, 11 within which is disposed, spaced from the walls 10, 11, an annular flame tube also having inner and outer walls 12, 13, the former being constructed of more than one part to permit the entry of air for cooling as shown.
- the inner and outer walls 10, 11 of the air jacket converge to form an inlet 14 at the upstream end and an outlet at the other, and the downstream end of the flame tube converges to form an outlet 15 to a turbine (not shown).
- a shield 16 Extending substantially obliquely across the interior of the flame tube and extending from the upstream end to a position near the downstream end but offset from the outlet 15, is a shield 16 defining with the inner wall 12 to which it is connected a combustion zone of generally toroidal form.
- this shield '16 Secured to the outside of this shield '16 and communicating with the interior thereof at the upstream end are a plurality of spaced ducts 17 which terminate at their outer edges at a position adjacent to but spaced from the outer wall 13 of the flame tube these ducts extending towards the flame tube outlet 15 as shown. Between adjacent ones of these duct 17 are defined passages 18 (refer to FIGURE 2) through which dilution air can enter to mix with products of combustion which leave the combustion zone through the ducts 17.
- a plurality of hollow vanes 19 Extending transversely across the combustion zone intermediate the upstream and downstream ends thereof, are a plurality of hollow vanes 19 having perforated sides, and disposed within each is a multiple fuel burner head 20 as seen in FIGURE 2.
- burner nozzles 21 At the downstream end of the combustion zone are burner nozzles 21 for supplying further fuel to the combustion zone.
- Primary air for combustion enters this zone, from the space defined between the inner wall 12 of the flame tube and the inner air jacket wall 10', through the vanes 19 where it becomes mixed with the fuel, and secondary air enters the chamber through a plurality of holes 22 in the inner wall 12.
- the products of combustion leave the combustion zone through the ducts 17 and become mixed with dilution air entering through the passages 18, and the mixed combustion products and dilution air then flow to the downstream end of the flame tube and out through the outlet 15.
- Combustion apparatus for a gas turbine engine comprising an annular air jacket having inner and outer walls terminating at positions to define an inlet and a outlet, an annular flame tube having inner and outer walls spaced from those of the air jacket respectively, said flame tube walls defining an outlet at the downstream end, a shield within the flame tube extending substantially obliquely across it from a position near the downstream end to the upstream end, it being connected to the inner Wall of the flame tube near the downstream end to define therewith a combustion zone, a plurality of spaced ducts communicating with the interior of the flame tube at the upstream end and extending within the outer wall of the flame tube towards the outlet, there being defined between adjacent ones of these ducts a plurality of passages communicating with the air jacket inlet whereby dilution air can enter the flame tube to mix with products of combustion leaving the combustion zone through the ducts, and there being a plurality of hollow vanes extending across the combus tion zone through openings in the inner flame tube wall and through which fuel and air for combustion can
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
Aug. 12, 1969 K. GREENWOOD 60,345
CQMBUSTION APPARATUS FOR GAS TURBINE ENGINES Filed Dec. 28. 1967 INVENTOR K. 5W4
BYMWAM ATTORNEYS United States Patent Ofice 3,460,345 Patented Aug. 12, 1969 3,460,345 COMBUSTION APPARATUS FOR GAS TURBINE ENGINES Kenneth Greenwood, 'Cliviger, near Burnley, England,
assignor to Joseph Lucas (Industries) Limited, Birmingham, England Filed Dec. 28, 1967, Ser. No. 694,234 Int. Cl. F02c 3/24, 3/14 US. Cl. 60-39.65 1 Claim ABSTRACT OF THE DISCLOSURE Combustion apparatus for a gas turbine engine comprising an annular air jacket, an annular flame tube in spaced relation within the air jacket, a shield within the flame tube extending obliquely across the flame tube from near the downstream end to the upstream end, the inner wall of the flame tube defining, with the shield a combustion zone, a plurality of spaced ducts extending from the combustion zone to the downstream end of the flame tube, a plurality of passages defined between the ducts, whereby dilution air can enter the flame tube to mix with air combustion products leaving the combustion zone from the ducts, and a plurality of vanes extending across the combustion zone through openings in which fuel and air can enter that zone.
This invention has for its object to provide combustion apparatus for gas turbine engines, in a convenient form.
According to the invention there is provided combustion apparatus for a gas turbine engine comprising an annular air jacket having inner and outer walls terminating at positions to define an inlet and an outlet, an annular flame tube having inner and outer walls spaced from those of the air jacket respectively, said flame tube walls defining an outlet at the downstream end, a shield within the flame tube extending substantially obliquely across it from a position near the downstream end to the upstream end, it being connected to the inner wall of the flame tube to define therewith a combustion zone, a plurality of spaced ducts communicating with the interior of the flame tube at the upstream end and extending within the outer wall of the flame tube towards the outlet, there being defined between adjacent ones of these ducts a plurality of passages communicating with the air jacket inlet whereby dilution air can enter the flame tube to mix with products of combustion leaving the combustion zone through the ducts, and there being a plurality of vanes extending across the combustion zone through openings in which fuel and air for combustion can enter the combustion zone.
An example of the invention is illustrated in the accompanying drawings in which FIGURE 1 is a lengthwise cross sectional view of combustion apparatus constructed in accordance with the invention and FIGURE 2 is a transverse cross sectional view on the line II--II in FIG- URE 1.
In this example there is provided combustion apparatus for a gas turbine engine comprising an annular air jacket having inner and outer walls 10, 11 within which is disposed, spaced from the walls 10, 11, an annular flame tube also having inner and outer walls 12, 13, the former being constructed of more than one part to permit the entry of air for cooling as shown.
The inner and outer walls 10, 11 of the air jacket converge to form an inlet 14 at the upstream end and an outlet at the other, and the downstream end of the flame tube converges to form an outlet 15 to a turbine (not shown). Extending substantially obliquely across the interior of the flame tube and extending from the upstream end to a position near the downstream end but offset from the outlet 15, is a shield 16 defining with the inner wall 12 to which it is connected a combustion zone of generally toroidal form. Secured to the outside of this shield '16 and communicating with the interior thereof at the upstream end are a plurality of spaced ducts 17 which terminate at their outer edges at a position adjacent to but spaced from the outer wall 13 of the flame tube these ducts extending towards the flame tube outlet 15 as shown. Between adjacent ones of these duct 17 are defined passages 18 (refer to FIGURE 2) through which dilution air can enter to mix with products of combustion which leave the combustion zone through the ducts 17.
Extending transversely across the combustion zone intermediate the upstream and downstream ends thereof, are a plurality of hollow vanes 19 having perforated sides, and disposed within each is a multiple fuel burner head 20 as seen in FIGURE 2. At the downstream end of the combustion zone are burner nozzles 21 for supplying further fuel to the combustion zone. Primary air for combustion enters this zone, from the space defined between the inner wall 12 of the flame tube and the inner air jacket wall 10', through the vanes 19 where it becomes mixed with the fuel, and secondary air enters the chamber through a plurality of holes 22 in the inner wall 12. The products of combustion leave the combustion zone through the ducts 17 and become mixed with dilution air entering through the passages 18, and the mixed combustion products and dilution air then flow to the downstream end of the flame tube and out through the outlet 15.
Having thus described my invention what I claim as new and desire to secure by Letters Patent is:
1. Combustion apparatus for a gas turbine engine comprising an annular air jacket having inner and outer walls terminating at positions to define an inlet and a outlet, an annular flame tube having inner and outer walls spaced from those of the air jacket respectively, said flame tube walls defining an outlet at the downstream end, a shield within the flame tube extending substantially obliquely across it from a position near the downstream end to the upstream end, it being connected to the inner Wall of the flame tube near the downstream end to define therewith a combustion zone, a plurality of spaced ducts communicating with the interior of the flame tube at the upstream end and extending within the outer wall of the flame tube towards the outlet, there being defined between adjacent ones of these ducts a plurality of passages communicating with the air jacket inlet whereby dilution air can enter the flame tube to mix with products of combustion leaving the combustion zone through the ducts, and there being a plurality of hollow vanes extending across the combus tion zone through openings in the inner flame tube wall and through which fuel and air for combustion can enter the combustion zone.
No references cited.
J'UL-IUS E. WEST, Primary Examiner US. Cl. X.R. 60-39
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US69423467A | 1967-12-28 | 1967-12-28 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| US3460345A true US3460345A (en) | 1969-08-12 |
Family
ID=24787970
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| US694234A Expired - Lifetime US3460345A (en) | 1967-12-28 | 1967-12-28 | Combustion apparatus for gas turbine engines |
Country Status (1)
| Country | Link |
|---|---|
| US (1) | US3460345A (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5207064A (en) * | 1990-11-21 | 1993-05-04 | General Electric Company | Staged, mixed combustor assembly having low emissions |
| US5239818A (en) * | 1992-03-30 | 1993-08-31 | General Electric Company | Dilution pole combustor and method |
| US5323605A (en) * | 1990-10-01 | 1994-06-28 | General Electric Company | Double dome arched combustor |
| WO1995020130A1 (en) * | 1994-01-24 | 1995-07-27 | Siemens Aktiengesellschaft | Combustion chamber for a gas turbine |
| WO2006053825A1 (en) * | 2004-11-16 | 2006-05-26 | Alstom Technology Ltd | Gas turbine system and associated combustion chamber |
| US8479492B2 (en) * | 2011-03-25 | 2013-07-09 | Pratt & Whitney Canada Corp. | Hybrid slinger combustion system |
-
1967
- 1967-12-28 US US694234A patent/US3460345A/en not_active Expired - Lifetime
Non-Patent Citations (1)
| Title |
|---|
| None * |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5323605A (en) * | 1990-10-01 | 1994-06-28 | General Electric Company | Double dome arched combustor |
| US5207064A (en) * | 1990-11-21 | 1993-05-04 | General Electric Company | Staged, mixed combustor assembly having low emissions |
| US5239818A (en) * | 1992-03-30 | 1993-08-31 | General Electric Company | Dilution pole combustor and method |
| WO1995020130A1 (en) * | 1994-01-24 | 1995-07-27 | Siemens Aktiengesellschaft | Combustion chamber for a gas turbine |
| US5735115A (en) * | 1994-01-24 | 1998-04-07 | Siemens Aktiengesellschaft | Gas turbine combustor with means for removing swirl |
| WO2006053825A1 (en) * | 2004-11-16 | 2006-05-26 | Alstom Technology Ltd | Gas turbine system and associated combustion chamber |
| US8479492B2 (en) * | 2011-03-25 | 2013-07-09 | Pratt & Whitney Canada Corp. | Hybrid slinger combustion system |
| US8677731B2 (en) | 2011-03-25 | 2014-03-25 | Pratt & Whitney Canada Corp. | Hybrid slinger combustion system |
| US9874148B2 (en) | 2011-03-25 | 2018-01-23 | Pratt & Whitney Canada Corp. | Hybrid slinger combustion system |
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