Pratt-Whitney Canada Corp

Si-Man Amy Lao

Sri Sreekanth

Michael Papple

Michael Leslie Clyde Papple

Michael Leslie Papple

Oleg Morenko

Tin-Cheung John Hu

Jeffrey Richard Verhiel

Hayley Ozem

Maximilian Baranowicz

Katherine Little

John Tin Cheung Hu

Jeffrey Verhiel

A support pin of a combustor assembly is provided. The combustor assembly includes a casing of a combustor and an igniter. The igniter includes a main section and a tip from which sparks generated by the igniter within the main section are ejected. The support pin includes an exterior section, a main body and a tip section. The exterior section is connectable to the casing. The igniter is affixable to the exterior section. The main body is integrally formed with the exterior section and is disposable to surround the main section of the igniter. The main body has a first wall thickness and defines support pin holes. The tip section is integrally formed with the main body and is disposable to surround the tip of the igniter. The tip section has a second wall thickness. The second wall thickness exceeds the first wall thickness.

Support pin for igniter assembly

A fuel nozzle assembly comprising an annular slot surrounding a fuel nozzle, the annular slot having gas passages for feeding a gas into the slot and against an opposing wall of the slot. A method of operating a gas turbine engine including directing a gas flow into and across the slot against an opposing wall of the slot to generate a circulating gas flow filling the slot, the gas flow passing into the slot through one or more gas outlets within the slot and thereafter said gas flow exiting the slot into the combustion chamber, the gas outlets spaced away from the closed end of the slot. A gas turbine engine comprising a slot formed in a fuel nozzle assembly, the slot having one or more gas passages extending through a wall of the slot and feeding a gas into the slot against a another wall of the slot.

Fuel nozzle with slot for cooling

A floating collar assembly is configured to receive a fuel nozzle or an igniter projecting through an opening defined in a combustor shell lined with heat shields having studs projecting through the combustor shell for engagement with corresponding fasteners outside the combustor shell. A floating collar is mounted outside the combustor shell with an opening in alignment with the opening in the combustor shell for receiving the fuel nozzle or the igniter. An external retaining bracket is mounted to the heat shield studs or other studs projecting outwardly from the combustor shell so as to trap the floating collar between the combustor shell and the bracket.

Combustor floating collar mounting arrangement

A cooling arrangement provides cooling around a dilution hole defined in a liner circumscribing a combustion chamber of a gas turbine engine. The cooling arrangement comprises a hollow boss projecting from an outer surface of the liner about the dilution hole. The hollow boss defines an internal cavity extending circumferentially around the dilution hole. The internal cavity has an inlet in fluid flow communication with an air plenum surrounding the liner and an outlet in fluid flow communication with the combustion chamber.

Internally cooled dilution hole bosses for gas turbine engine combustors

A combustor heat shield comprises a panel body having a front surface and a back surface. The back surface has sealing rails extending therefrom and defining a serpentine cooling path on the back surface of the panel body.

Combustor heat shield cooling

A gas turbine engine combustor has a shell defining a combustion chamber having a primary zone and a dilution zone downstream of the primary zone. The shell has an outer skin and an inner skin defining an air gap therebetween. The inner skin in the upstream portion of the primary zone is free from effusion holes and has heat transfer augmenters projecting from a back side thereof into the air gap. Effusion holes in the inner skin are only disposed downstream towards the tail end of the primary zone in order to delay the injection of any disruptive cooling air that could potentially interfere with the combustion process.

Combustor primary zone cooling flow scheme

A turbine component has a plurality of cooling passages each extending through a body of a structure between opposite hot and cold surfaces of the structure. According to one embodiment, at least one of the cooling passages includes a plurality of upstream paths defining respective inlet openings on the cold surface and merging into a number of downstream paths defining respective outlet openings on the hot surface.

Cooling passages in a turbine component

A combustor heat shield comprises a panel body having a front surface and a back surface. The back surface has rail-less edges and a turbulator band extending inwardly from the rail-less edges. The band includes a plurality of turbulators defining tortuous cooling paths up to the rail-less edges. Effusion holes are distributed over the central area.

Combustor heat shield edge cooling

A combustor heat shield has a heat shield body having a first surface configured to face a combustor shell and an opposed second surface configured to face towards the combustion gases in the combustion chamber. A dilution or igniter hole is defined in the heat shield body. An array of circumferentially spaced-apart cooling holes is provided around the at least one dilution or igniter hole. The cooling holes are oriented to locally deliver a swirl of cooling air around an axis of the dilution or igniter hole. The cooling holes are angled relative to the heat shield body and extend from an inlet on the first surface to an outlet on the second surface. The outlet is positioned closer to a perimeter of the dilution or igniter hole than the inlet.

Combustor heat shield cooling hole arrangement

A turbine component includes a structure having hot and cold surfaces opposite each other; and a plurality of cooling holes extending between the cold and hot surfaces, each of the cooling holes including at least one projection or recess element to form part of a fluid path surface with enhanced in-hole heat convection.

Effusion cooling holes

A combustor for a gas turbine engine comprises a single skin liner defining a combustion chamber. The single skin liner has an inner surface facing the combustion chamber and an outer surface exposed to a coolant flow discharged in a plenum extending from the outer surface of the single skin liner to the engine casing. Cooling holes extend through the single skin liner. Cooling protuberances, such as fins or pin fins, project integrally from the outer surface of the single skin liner into the plenum, the cooling fins being interspersed between the cooling holes.

Growing community of inventors

Mississauga, Canada

Si-Man Amy Lao