Trailing edge fuel injection enhancement for flame holding mitigation
An injector for a combustor of a gas turbine engine is provided with a plurality of first vanes radially arrayed about a central axis of the injector and a plurality of second vanes radially arrayed about the central axis of the injector and disposed radially inward of the plurality of first vanes. A plurality of fuel injection holes are disposed nearer to a trailing edge than to a leading edge of the second vanes for injecting fuel into compressed air passing through over the second vanes. The trailing edge of each of the second vanes includes a non-planar profile configured to induce turbulence in the compressed air to thereby mix the fuel with the compressed air and reduce the surfaces on which undesirable flame anchoring may occur.
1. An injector for a combustor of a gas turbine engine, the injector comprising:
a plurality of first vanes radially arrayed about a central axis of the injector;
a plurality of second vanes radially arrayed about the central axis of the injector and disposed radially inward of the plurality of first vanes, each of the plurality of second vanes including:
a leading edge;
a trailing edge including a stepped profile comprising:
a radially outer first portion having a first length in a radial direction;
a radially intermediate second portion having a second length in the radial direction; and
a radially inner third portion having a third length in the radial direction,
the second length being greater than the third length, and the third length being greater than the first length,
the radially intermediate second portion including a second trailing end circumferentially offset from a first trailing end of the radially outer first portion and a third trailing end of the radially inner third portion;
a plurality of fuel injection holes disposed on the radially intermediate second portion nearer to the trailing edge than to the leading edge and configured to inject fuel into compressed air passing over the second vane; and
a fuel feed hole in fluid communication with the plurality of fuel injection holes and configured to supply the fuel to the plurality of fuel injection holes,
wherein the trailing edge stepped profile is configured to induce turbulence in the compressed air to thereby mix the fuel with the compressed air.
2. The injector of claim 1 , further comprising a first relief cut disposed between the radially outer first portion and the radially intermediate second portion and a second relief cut disposed between the radially intermediate second portion and the radially inner third portion.
3. The injector of claim 1 , wherein the third trailing end of the radially inner third portion includes a portion of a substantially sinusoidal shape.
4. The injector of claim 1 , wherein the fuel feed hole includes a tear-drop shaped cross-section profile.
5. The injector of claim 1 , wherein each of the plurality of first vanes includes an elliptical cross-sectional profile.
6. A combustor for a gas turbine engine, the combustor comprising:
a combustion liner defining a combustion zone therein; and
a first injector surrounding the combustion liner and comprising:
a plurality of first vanes radially arrayed about a central axis of the injector, each of the first vanes separated from an adjacent one of the first vanes by one of a plurality of first passages forming part of a radially outer flow path;
a plurality of second vanes radially arrayed about the central axis of the injector and disposed radially inward of the plurality of first vanes, each of the second vanes separated from an adjacent one of the second vanes by one of a plurality of second passages forming part of a radially inner flow path, each of the plurality of second vanes including:
a leading edge;
a trailing edge including a stepped profile comprising:
a radially outer first portion having a first length in a radial direction;
a radially intermediate second portion having a second length in the radial direction; and
a radially inner third portion having a third length in the radial direction,
the second length being greater than the third length, and the third length being greater than the first length,
the radially intermediate second portion including a second trailing end circumferentially offset from a first trailing end of the radially outer first portion and a third trailing end of the radially inner third portion;
a plurality of fuel injection holes disposed on the radially intermediate second portion nearer to the trailing edge than to the leading edge and configured to inject fuel into compressed air passing through the radially inner flow path; and
a fuel feed hole in fluid communication with the plurality of fuel injection holes and configured to supply the fuel to the plurality of fuel injection holes,
wherein the trailing edge stepped profile is configured to induce turbulence in the compressed air passing through the radially inner flow path to thereby mix the fuel with the compressed air upstream the combustion chamber.
7. The combustor of claim 6 , further comprising a first relief cut disposed between the radially outer first portion and the radially intermediate second portion and a second relief cut disposed between the radially intermediate second portion and the radially inner third portion.
8. The combustor of claim 6 , wherein the third trailing end of the radially inner third portion includes a portion of a substantially sinusoidal shape.
9. The combustor of claim 6 , further comprising a second injector downstream of the first injector along the radially outer flow path, the second injector being configured to mix fuel with compressed air passing through the radially outer flow path to thereby mix the fuel with the compressed air upstream of the combustion chamber.
10. The combustor of claim 9 , wherein the fuel feed hole includes a tear-drop shaped cross-section profile.
11. The combustor of claim 9 , wherein each of the plurality of first vanes includes an elliptical cross-sectional profile.