Pratt-Whitney Canada Corp

Tin-Cheung John Hu

Richard Freer

Kian McCaldon

Michel Bousquet

André Fortin

Oleg Morenko

Michael Papple

Sri Sreekanth

Robert Sze

Si-Man Amy Lao

Nassim Bedrani

A method of servicing a gas turbine engine having an igniter socket, the method comprising: inserting a glow plug into the igniter socket of the gas turbine engine until a rod end of a glow plug heater rod of the glow plug is exposed to a combustion chamber of the gas turbine engine; and blocking a gap between the glow plug heater rod and an aperture defined in a combustor liner of the gas turbine engine to block fluid communication between the combustion chamber and an environment outside the combustion chamber via the aperture.

Igniter for gas turbine engine

An aircraft engine has a combustor supplied by a hydrogen fuel system and is configured to combust hydrogen and generate water vapor. A water vapor collector receives at least part of the water vapor. A condenser is in fluid communication with the water vapor collector to receive and cool in the condenser the at least part of the water vapor and thereby condense at least part of the at least part of the flow of water vapor. A spray nozzle is in fluid communication with the condenser and operable to spray the condensed part of the at least part of the flow of water vapor onto a component of the aircraft engine.

Aircraft engine with hydrogen fuel system

A combustor of an aircraft engine comprises a liner defining a primary and a dilution zone having a hot surface exposed to a flow of combustion gases traveling from the primary zone downstream to the dilution zone and a cold surface. Dilution holes extending through the liner from the cold to the hot surface delimit the primary from the dilution zone. Effusion holes extending through the liner from the cold to the hot surface direct cooling air into the dilution zone. Two or more rows of effusion holes positioned within three dilution hole diameters downstream of the dilution holes are oriented relative to the liner to direct the cooling air in a cooling direction that is at least one of normal to the direction of the flow of gases passing adjacent the effusion holes, and against the direction of the flow of gases passing adjacent the effusion holes.

Combustor with dilution holes

A gas turbine engine has: a casing; a combustor liner delimiting a combustion chamber; a fuel nozzle in fluid communication with the combustion chamber; and an igniter having a base, a glow plug heater rod extending from the base along an axis and terminating in a rod end, and a sleeve extending around the glow plug heater rod, the sleeve radially spaced apart from the glow plug heater rod by an annular gap, the sleeve defines fins circumferentially distributed around the axis, each two circumferentially adjacent fins of the fins spaced apart from one another by a spacing communicating with the annular gap, the fins extending in a direction having an axial component from roots to tips, the roots axially closer to the base than the tips, the rod end extending axially beyond the tips of the fins such that the rod end is located outside the annular gap.

Wall assemblies for a combustor of a gas turbine engine are disclosed. A wall assembly comprises an outer shell made of a metallic material, adjacent first and second inner panels mounted to the outer shell via an insert and a damper disposed between the outer shell and at least one of the first and second inner panels. The first and second inner panels may be spaced apart from the outer shell to define a double-wall configuration with the outer shell. The first and second inner panels may be made of a composite material. The insert may be made from substantially the same or other type of composite material.

Combustor wall assembly for gas turbine engine

There is disclosed an igniter for a gas turbine engine including: a base, a glow plug heater rod extending from the base along an axis and terminating in a rod end, and a plurality of fins disposed circumferentially around the glow plug heater rod, the fins extending axially along at least a portion of the glow plug heater rod. A gas turbine engine including such an igniter is further disclosed.

A combustor for a gas turbine engine comprises a combustor chamber defined at least partially by an outer combustor skin and an inner combustor skin. A plurality of stand-off devices have a body including a first end and a second end, the second end of the body retained in an opening in the outer combustor skin, the first end spaced apart from the second end and abutting the inner combustor skin to space the inner combustor skin apart from the outer combustor skin.

Stand-off device for double-skin combustor liner

There is disclosed an igniter for a gas turbine engine including: a base including a securing assembly configured to be matingly connected to a casing of the gas turbine engine, a glow plug heater rod, the glow plug heater rod extending from the base along an axis and terminating in a rod end, a flow impeding member extending along the axis and having a distal end spaced from the base and extending axially relative to the axis beyond the rod end, the flow impeding member sized and configured such that the distal end extends into a combustion chamber of the gas turbine engine upon the base connected to the casing.

There is disclosed an igniter for a gas turbine engine including: a base, a glow plug heater rod, the heater rod extending from the base along an axis and terminating in a rod end, a peripheral wall extending circumferentially around the rod end and having a distal end directed away from the base, a gap between the peripheral wall and the heater rod, the rod end being axially retracted relative the distal end of the peripheral wall.

A ring assembly for holding a double-skin combustor liner has an inner skin of ceramic matrix composite and an outer skin. The assembly comprises an annular end body, a first projecting portion projecting relative to the annular end body at least partially in an axial direction, the first projecting portion configured for supporting the inner skin, a second projecting portion projecting relative to the annular end body at least partially in the axial direction, the second projecting portion configured for supporting the outer skin. The first and second projecting portions are radially spaced apart to provide a radial spacing between the inner skin and the outer skin. An expansion joint is between the ring assembly and the inner skin configured to permit motion resulting from a variation in thermal expansion between the inner skin and the ring assembly.

Ring assembly for double-skin combustor liner

There is disclosed a method of servicing a gas turbine engine having a spark plug igniter connected to a spark plug igniter socket of the engine, the method including: removing the spark plug from the spark plug igniter socket of the gas turbine engine; inserting a glow plug igniter having a base configured for matingly engaging the spark plug igniter socket; and securing the glow plug igniter to the gas turbine engine.

There is disclosed an igniter for a gas turbine engine including: a base including a securing assembly configured to be matingly connected to a casing of the gas turbine engine, a glow plug heater rod extending from the base along an axis to a rod end distal from the base, the glow plug heater rod sized such that that the rod end is exposed to a combustion chamber of the gas turbine engine when the base is connected to the casing.

There is disclosed an igniter for a gas turbine engine including: a base including a securing assembly configured to be matingly connected to a casing of the gas turbine engine, a glow plug heater rod extending from the base along an axis and terminating in a rod end, a combustor liner plug extending circumferentially around the heater rod, the combustor liner plug being sized and configured to extend inside an aperture in a combustor liner of the gas turbine engine when the base is connected to the casing between the heater rod and a periphery of the aperture.

There is disclosed an igniter for a gas turbine engine including: a base, a glow plug heater rod, the glow plug heater rod extending from the base along an axis and terminating in a rod end, a sleeve extending circumferentially around the glow plug heater rod along at least a portion of a length of the glow plug heater rod, the sleeve having an inner surface spaced from the glow plug heater rod to provide a gap between the inner surface and the glow plug heater rod, the gap extending radially relative to said axis.

There is disclosed an igniter for a gas turbine engine including: a base; a glow plug heater rod extending from the base along an axis and terminating in a rod end; and a structure having open porosity disposed adjacent the glow plug heater rod. A method of operating the igniter and a gas turbine engine having such an igniter are also disclosed.

Growing community of inventors

Markham, Canada

Tin-Cheung John Hu