A combustor assembly for a gas turbine engine includes a liner and a combustor dome. The combustor dome and liner together at least in part define a combustion chamber. The combustor dome includes a transition portion and a forward wall. The transition portion extends from the forward wall towards the liner. Additionally the transition portion may define an angle relative to the forward wall and/or may define a radius of curvature between the forward wall of the combustor dome and a flat of the transition portion of the combustor dome for increasing an aerodynamic efficiency of the combustor dome.

A new dual-mode ramjet combustor used for operation over a wide flight Mach number range is described. Subsonic combustion mode is usable to lower flight Mach numbers than current dual-mode scramjets. High speed mode is characterized by supersonic combustion in a free-jet that traverses the subsonic combustion chamber to a variable nozzle throat. Although a variable combustor exit aperture is required, the need for fuel staging to accommodate the combustion process is eliminated. Local heating from shock-boundary-layer interactions on combustor walls is also eliminated.

A new dual-mode ramjet combustor used for operation over a wide flight Mach number range is described. Subsonic combustion mode is usable to lower flight Mach numbers than current dual-mode scramjets. High speed mode is characterized by supersonic combustion in a free-jet that traverses the subsonic combustion chamber to a variable nozzle throat. Although a variable combustor exit aperture is required, the need for fuel staging to accommodate the combustion process is eliminated. Local heating from shock-boundary-layer interactions on combustor walls is also eliminated.

Provided is a combustor assembly. The combust assembly includes: a plurality of swirlers through which a first fluid that is a part of a fluid discharged from a compressor passes; a base portion, in which the plurality of swirlers are provided, comprising a first through hole formed between one swirler and another swirler from among the plurality of swirlers so that a second fluid that is another part of the fluid discharged from the compressor and different from the first fluid passes through the first through hole; and a deflector provided in the base portion so as to face the first through hole for changing a moving direction of the second fluid.

Provided is a combustor assembly. The combust assembly includes: a plurality of swirlers through which a first fluid that is a part of a fluid discharged from a compressor passes; a base portion, in which the plurality of swirlers are provided, comprising a first through hole formed between one swirler and another swirler from among the plurality of swirlers so that a second fluid that is another part of the fluid discharged from the compressor and different from the first fluid passes through the first through hole; and a deflector provided in the base portion so as to face the first through hole for changing a moving direction of the second fluid.

A dynamic pressure exchanger configured for a combustion process includes an inlet plate and a rotor assembly mounted for rotation relative to the inlet plate about a central axis of the dynamic pressure exchanger. The inlet plate is formed to include an inlet port configured to direct air into the rotor assembly. The rotor assembly includes an inner rotor and an outer rotor arranged around the inner rotor.

A dynamic pressure exchanger configured for a combustion process includes an inlet plate and a rotor assembly mounted for rotation relative to the inlet plate about a central axis of the dynamic pressure exchanger. The inlet plate is formed to include an inlet port configured to direct air into the rotor assembly. The rotor assembly includes an inner rotor and an outer rotor arranged around the inner rotor.

An apparatus for an impingement hole for an engine component of a gas turbine engine includes an impingement baffle. The impingement baffle is spaced from an impingement surface and includes a plurality of impingement holes for providing an impingement flow to the impingement surface. The impingement holes can have an angled upstream edge such that an inlet has a greater cross-sectional area than an outlet. The walls of the impingement holes can have a hood to provide a higher shear flow content to minimize dust accumulation on the impingement surface.

An apparatus for an impingement hole for an engine component of a gas turbine engine includes an impingement baffle. The impingement baffle is spaced from an impingement surface and includes a plurality of impingement holes for providing an impingement flow to the impingement surface. The impingement holes can have an angled upstream edge such that an inlet has a greater cross-sectional area than an outlet. The walls of the impingement holes can have a hood to provide a higher shear flow content to minimize dust accumulation on the impingement surface.

Superalloy material components for turbine engines, including steam and combustion turbine engines are fabricated by superplastic formation of a laser-sintered preform. Superalloy material powder is sintered into a preform, such as by laser sintering. The preform is inserted within a pressurized forming furnace, containing a mold with a mold cavity defined by a mold cavity surface. The preform is heated in the forming furnace, and differential pressure is applied across the preform to deform it superplastically into abutting contact with the mold cavity surface, without fracturing the preform. Thereafter, the superalloy component is extracted from the forming furnace.