BACKGROUND

The subject matter disclosed herein generally relates to gas turbine engines and, more particularly, to a method and apparatus for mitigating heat in cooling surfaces of gas turbine engines.

In one example, a combustor of a gas turbine engine may be configured to burn fuel in a combustion area. Such configurations may place substantial heat load on the structure of the combustor (e.g., heat shield panels, shells, etc.). Such heat loads may dictate that special consideration is given to structures, which may be configured as heat shields or panels, and to the cooling of such structures to protect these structures. Excess temperatures at these structures may lead to oxidation, cracking, and high thermal stresses of the heat shields panels.

SUMMARY

Disclosed is a gas turbine engine, the gas turbine engine including: a diffuser case defining an inner shroud and an outer shroud; and a combustor housed within the diffuser case between the inner shroud and the outer shroud, the combustor including: a shell; a forward dome attached to the shell at a forward end of the combustor; and a deflector attached to the forward dome and extending away from the forward dome.

In addition to one or more of the features described above, or as an alternative to any of the foregoing embodiments, the deflector extends aft-ward and in a radially inward direction away from the forward dome and into the inner shroud.

In addition to one or more of the features described above, or as an alternative to any of the foregoing embodiments, the deflector is attached to a radially inward side of the forward dome.

In addition to one or more of the features described above, or as an alternative to any of the foregoing embodiments, the forward dome further includes: a curved dome portion; and a radially inward linear portion, the forward dome being attached to the shell at the radially inward linear portion, wherein the forward dome transitions from the curved dome portion to the radially inward linear portion at a radially inward transition point, and wherein the deflector is attached to the forward dome proximate the radially inward transition point.

In addition to one or more of the features described above, or as an alternative to any of the foregoing embodiments, the deflector is a solid body.

In addition to one or more of the features described above, or as an alternative to any of the foregoing embodiments, the deflector further includes: a radially inward forward side; a radially outward aft side opposite the radially inward forward side; and one or more orifices extending from the radially inward forward side to the radially outward aft side.

In addition to one or more of the features described above, or as an alternative to any of the foregoing embodiments, the one or more orifices are oriented at an angle less than or equal to 90 degrees relative to the radially inward forward side.

In addition to one or more of the features described above, or as an alternative to any of the foregoing embodiments, the one or more orifices include corners that are rounded in shape, the corners being adjacent to at least one of the radially inward forward side and the radially outward aft side.

In addition to one or more of the features described above, or as an alternative to any of the foregoing embodiments, a catcher is located opposite of the deflector on a radially inward wall of the diffuser case, the catcher forming an internal chamber with the radially inward wall, wherein the catcher comprises a forward opening to allow particulate to enter into the internal chamber.

In addition to one or more of the features described above, or as an alternative to any of the foregoing embodiments, the catcher further includes a rear backstop located aft of the forward opening.

In addition to one or more of the features described above, or as an alternative to any of the foregoing embodiments, a radially inward exit orifice in the radially inward wall, the radially inward exit orifice being fluidly connected to the internal chamber of the catcher.

In addition to one or more of the features described above, or as an alternative to any of the foregoing embodiments, the deflector is oriented at an angle relative to a longitudinal axis of the gas turbine engine about equal to an angle of the curved dome portion proximate the radially inward transition point relative to the longitudinal axis of the gas turbine engine.

Also disclosed is a combustor for use in a gas turbine engine, the combustor including: a shell; a forward dome attached to the shell at a forward end of the combustor; and a deflector attached to the forward dome and extending away from the forward dome.

In addition to one or more of the features described above, or as an alternative to any of the foregoing embodiments, the deflector extends aft-ward and in a radially inward direction away from the forward dome.

In addition to one or more of the features described above, or as an alternative to any of the foregoing embodiments, the deflector is attached to a radially inward side of the forward dome.

In addition to one or more of the features described above, or as an alternative to any of the foregoing embodiments, the forward dome further includes: a curved dome portion; and a radially inward linear portion, the forward dome being attached to the shell at the radially inward linear portion, wherein the forward dome transitions from the curved dome portion to the radially inward linear portion at a radially inward transition point, and wherein the deflector is attached to the forward dome proximate the radially inward transition point.

In addition to one or more of the features described above, or as an alternative to any of the foregoing embodiments, the deflector is a solid body.

In addition to one or more of the features described above, or as an alternative to any of the foregoing embodiments, the deflector further includes: a radially inward forward side; a radially outward aft side opposite the radially inward forward side; and one or more orifices extending from the radially inward forward side to the radially outward aft side.

In addition to one or more of the features described above, or as an alternative to any of the foregoing embodiments, the one or more orifices are oriented at an angle less than or equal to 90 degrees relative to the radially inward forward side.

In addition to one or more of the features described above, or as an alternative to any of the foregoing embodiments, the one or more orifices include corners that are rounded in shape, the corners being adjacent to at least one of the radially inward forward side and the radially outward aft side.

The foregoing features and elements may be combined in various combinations without exclusivity, unless expressly indicated otherwise. These features and elements as well as the operation thereof will become more apparent in light of the following description and the accompanying drawings. It should be understood, however, that the following description and drawings are intended to be illustrative and explanatory in nature and non-limiting.

