Claims
- 1. Annular combustion equipment for a gas turbine engine comprising an inner annular wall, an outer annular wall and an upstream wall, the upstream wall comprising a single skin and forming part of a dump diffuser, the upstream wall being convectively cooled by cooling and dilution air supplied from the dump diffuser passing over the upstream surface of the upstream wall, the upstream wall having a plurality of circumferentially arranged equi-spaced apertures, each aperture having a convergent/divergent pot positioned coaxially therewith, each convergent/divergent pot being secured at its downstream end to the upstream wall and extending in an upstream direction therefrom, each convergent/divergent pot having a radial swirler assembly positioned coaxially at its upstream end to supply primary air through the convergent/divergent pot into the combustion equipment, each convergent/divergent pot having a fuel injector aligned therewith to supply fuel through the convergent/divergent pot into the combustion equipment, each convergent/divergent pot having an annular air scoop positioned coaxially around the convergent/divergent pot and each annular air scoop being secured to and extending in an upstream direction from the upstream wall, and having an annular upstream end positioned axially adjacent to said radial swirler assembly, an annular chamber being formed between each convergent/divergent pot and the corresponding annular air scoop, each convergent/divergent pot having a plurality of apertures arranged in a ring at its downstream end for supplying cooling air from the annular chamber over the downstream face of the upstream wall, each annular air scoop supplying primary air to the radial swirler assembly of the respective convergent/divergent pot and cooling air to the respective annular chamber, a plurality of said annular air scoops being provided in a circumferentially spaced relation to each other such that the upstream wall between adjacent air scoops is convectively cooled by cooling and dilution air passing over the upstream surface of the upstream wall.
- 2. Annular combustion equipment for a gas turbine engine as claimed in claim 1 in which the upstream wall has a curved cross-section, the downstream end of each convergent/divergent pot is curved to correspond to the curving of the upstream wall.
- 3. Annular combustion equipment for a gas turbine engine as claimed in claim 1 in which the upstream wall is flat in cross-section, the downstream end of each convergent/divergent pot is flat to correspond to the upstream wall.
- 4. Annular combustion equipment for a gas turbine engine as claimed in claim 1 in which the divergent portion of the convergent/divergent pot has a circular cross-section.
- 5. Annular combustion equipment for a gas turbine engine as claimed in claim 4 in which the divergent portion of the convergent/divergent pot is conical.
- 6. Annular combustion equipment for a gas turbine engine as claimed in claim 1 in which the divergent portion of the convergent/divergent pot has internal chambers supplied with cooling air from the annular chamber for cooling of the pot.
- 7. Annular combustion equipment for a gas turbine engine as claimed in claim 1 in which a second radial swirler assembly is positioned coaxially with and axially between the convergent/divergent pot and the first radial swirler assembly, and an annular lip is positioned between the first and second swirler assemblies and extends radially inwards and in a downstream direction into the convergent/divergent pot, the fuel injector and the first radial swirler assembly supply fuel and air into the convergent/divergent pot through the annular lip, and the second radial swirler assembly supplies air into the convergent/divergent pot and the annular lip deflects air from the second radial swirler assembly to flow over the convergent/divergent pot to prevent fuel depositing onthe convergent/divergent pot.
- 8. Annular combustion equipment for a gas turbine engine as claimed in claim 1 in which the upstream end of each annular air scoop is positioned upstream of the or each corresponding radial swirler assembly to supply air to the or each radial swirler assembly and annular chamber.
- 9. Annular combustion equipment for a gas turbine engine as claimed in claim 1 in which the fuel injectors are located coaxially with the convergent/divergent pot and radial swirler assembly by locating means which allows relative movement of the fuel injector and the convergent/divergent pot axially, radially and circumferentially to limit the transmission of loads to the fuel injector.
- 10. Annular combustion equipment for a gas turbine engine as claimed in claim 9 in which the fuel injectors have partially spherical outer surfaces.
- 11. Annular combustion equipment for a gas turbine engine as claimed in claim 10 in which the locating means comprises a ring having a T section which abuts the partially spherical outer surface of the fuel injector, the stem of the T section ring extending into a slot formed between the upstream end of the radial swirler assembly and an annular member secured to and positioned coaxially with the radial swirler assembly.
- 12. Annular combustion equipment for a gas turbine engine as claimed in claim 10 in which the locating means comprises a ring having a T section and a split ring having a partially spherical inner surface, the split ring being positioned coaxially within and abutting the T section ring and the partially spherical inner surface of the split ring abutting the partially spherical outer surface of the fuel injector, the stem of the T section ring extending into a slot formed between the upstream end of the radial swirler assembly and an annular member secured to and positioned coaxially with the radial swirler assembly.
- 13. Annular combustion equipment for a gas turbine engine as claimed in claim 9 in which the locating means comprises a ring having a partially spherical outer surface which fits coaxially around the fuel injector, a pair of L section rings which have partially spherical inner surfaces which abut the partially spherical outer surface of the ring, the L section rings being positioned back to back and extending into a slot formed between the upstream end of the radial swirler assembly and an annular member secured to and positioned coaxially with the radial swirler assembly.
- 14. Annular combustion equipment for a gas turbine engine as claimed in claim 1 in which the fuel injector is an airspray fuel injector.
- 15. Annular combustion equipment for a gas turbine engine as claimed in claim 1 wherein each annular air scoop has an annular upstream end positioned upstream of the radial swirler assembly of each convergent/divergent pot, said annular upstream end of each annular air scoop being positioned axially adjacent the upstream end of the radial swirler assembly.
- 16. Annular combustion equipment for a gas turbine engine comprising an inner annular wall, an outer annular wall and an upstream wall, the upstream wall comprising a single skin and forming part of a dump diffuser, the upstream wall being convectively cooled by cooling and dilution air supplied from the dump diffuser passing over the upstream surface of the upstream wall, the upstream wall having a plurality of circumferentially arranged equi-spaced apertures, each aperture having a convergent/divergent pot positioned coaxially therewith, each convergent/divergent pot being secured at its downstream end to the upstream wall and extending in an upstream direction therefrom, each convergent/divergent pot having a radial swirler assembly positioned coaxially at its upstream end to supply primary air through the convergent/divergent pot into the combustion equipment, each convergent/divergent pot having a fuel injector aligned therewith to supply fuel through the convergent/divergent pot into the combustion equipment, each convergent/divergent pot having an annular air scoop positioned coaxially around the convergent/divergent pot and each annular air scoop being secured to and extending in an upstream direction from the upstream wall, the annular upstream end of each annular air scoop being positioned axially adjacent the downstream end of the radial swirler assembly, an annular chamber being formed between each convergent/divergent pot and the corresponding annular air scoop, each convergent/divergent pot having a plurality of apertures arranged in a ring at its downstream end for supplying cooling air from the annular chamber over the downstream face of the upstream wall, each annular air scoop supplying primary air to the radial swirler assembly of the respective convergent/divergent pot and cooling air to the respective annular chamber.
Priority Claims (1)
Number |
Date |
Country |
Kind |
8331634 |
Nov 1983 |
GBX |
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Parent Case Info
This is a continuation of application Ser. No. 671,785, filed Nov. 15, 1984 which was abandoned upon the filing hereof.
US Referenced Citations (11)
Foreign Referenced Citations (3)
Number |
Date |
Country |
1297244 |
Nov 1972 |
GBX |
1427146 |
Mar 1976 |
GBX |
1597817 |
Sep 1981 |
GBX |
Non-Patent Literature Citations (1)
Entry |
Le Febvre, Arthur H., Gas Turbine Combustion, 9/1983, pp. 8 and 100-102. |
Continuations (1)
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Number |
Date |
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Parent |
671785 |
Nov 1984 |
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