PRATT & WHITNEY CANADA CORP. patent applications on August 8th, 2024
Patent Applications by PRATT & WHITNEY CANADA CORP. on August 8th, 2024
PRATT & WHITNEY CANADA CORP.: 19 patent applications
PRATT & WHITNEY CANADA CORP. has applied for patents in the areas of F23R3/28 (14), F02C7/22 (8), F23R3/00 (2), F23D14/82 (2), F23R3/14 (1) F23R3/286 (13), F23R3/28 (2), B64F5/40 (1), F02C7/04 (1), F02C7/22 (1)
With keywords such as: fuel, mixing, chamber, air, into, gas, passages, nozzle, hydrogen, and combustion in patent application abstracts.
Patent Applications by PRATT & WHITNEY CANADA CORP.
Inventor(s): Daniel MACKAY of Thornhill (CA) for pratt & whitney canada corp.
IPC Code(s): B64F5/40, B60L9/00, B60L50/50, B60L53/16, B64D27/24, B64F1/36
CPC Code(s): B64F5/40
Abstract: a system for an aircraft, comprises an electric energy module; and a connector module operatively connected to the electric energy module. the connector module is: structured to attach the electric energy module to the aircraft when the connector module in an engaged mode while in use, and operable between the engaged mode and a disengaged mode, the connector module in the disengaged mode while in use disengaging the electric energy module from the aircraft.
20240263581. HIGH SHEAR FUEL DISTRIBUTOR_simplified_abstract_(pratt & whitney canada corp.)
Inventor(s): Kian McCaldon of Orangeville (CA) for pratt & whitney canada corp.
IPC Code(s): F02C7/04, F02C3/14, F02C7/22, F02C7/236
CPC Code(s): F02C7/04
Abstract: a fuel mixture distributor for a turbine engine assembly includes a mixing chamber that is disposed about a central axis from a back wall to an outlet of a combustion chamber, and a fuel inlet that extends into the mixing chamber along the central axis. the fuel inlet includes a plurality of fuel openings that are angled relative to the central axis and a first air inlet that encircles the mixing chamber and is spaced apart from the fuel inlet. the first air inlet includes a plurality of first air openings that introduce a first air flow into the mixing chamber. a second air inlet introduces a secondary air flow that is axially forward of the fuel inlet and the first air inlet and proximate to the outlet of the mixing chamber.
Inventor(s): Tin Cheung John Hu of Markham (CA) for pratt & whitney canada corp.
IPC Code(s): F02C7/22
CPC Code(s): F02C7/22
Abstract: an injector for a gas turbine engine includes an annular gas nozzle, a hydrogen feed conduit, and a disc. the annular gas nozzle is disposed along a central nozzle axis and includes a forward face, a frustoconical interior surface, and gas feed conduits that open at the frustoconical interior surface. the hydrogen feed conduit extends along the central nozzle axis through the annular gas nozzle. the hydrogen feed conduit and the frustoconical interior surface define there between an annular mixing chamber. the hydrogen feed conduit has an end portion that is axially displaced from the forward face. the end portion includes feed holes that open into the mixing chamber. the disc is disposed on the end portion and is diametrically larger than the end portion so as to form a forward boundary of the annular mixing chamber. the disc may have multiple teeth, serrated edges, single or multiple bleed holes that are normal or angularly drilled to enhance fuel and air mixing, and improve flame stability.
Inventor(s): Tin Cheung John Hu of Markham (CA) for pratt & whitney canada corp.
IPC Code(s): F23R3/28, F02C7/22
CPC Code(s): F23R3/28
Abstract: a gas turbine engine includes an annular combustion chamber and an injector ring that is configured to introduce a hydrogen and gas mixture into the combustion chamber. the injector ring may include a hydrogen manifold cavity, hydrogen feed conduits that extend off of the hydrogen manifold cavity and open into a mixing region at an axial end of the injector ring, and gas feed conduits that also open into the mixing region to supply gas that mixes with the hydrogen. the hydrogen feed conduits may be tangentially-sloped, and the gas feed conduits may be radially and tangentially sloped.
Inventor(s): Tin Cheung John Hu of Markham (CA) for pratt & whitney canada corp.
IPC Code(s): F23R3/28, F02C7/22
CPC Code(s): F23R3/28
Abstract: an injector for introducing hydrogen and air into a combustion chamber of a gas turbine engine includes a convergent-divergent nozzle head, a fairing, a fuel nozzle, and an air nozzle. the convergent-divergent nozzle head has in fluid communication in series a convergent section, a throat, and a divergent section. the fairing extends through the convergent section and through the throat to define an annular passage between the fairing and the convergent-divergent nozzle head that has an outlet in the divergent section. the fuel nozzle has multiple feed conduits that open to the annular passage for providing hydrogen fuel. the gas nozzle is upstream of the convergent-divergent nozzle head for providing gas into the annular passage.
Inventor(s): Kian McCaldon of Orangeville (CA) for pratt & whitney canada corp.
IPC Code(s): F23R3/28, F02C7/22
CPC Code(s): F23R3/286
Abstract: a fuel mixture distribution system for a turbine engine assembly includes a combustor that includes a wall defining a combustion chamber, a fuel mixture distributor that includes a mixing chamber that extends along an axis between a closed end and an exit opening to the combustion chamber, the mixing chamber shape being defined to achieve the desired mixing and prevent flashback at all operating conditions, and a plurality of fuel passages and a plurality of air passages that are disposed about a periphery of the mixing chamber within a common plane transverse to the axis. each of the plurality of fuel passages and each of the plurality of air passages are angled to induce mixing of fuel and air within the mixing chamber prior to flowing through the exit opening into the combustion chamber.
Inventor(s): Kian McCaldon of Orangeville (CA) for pratt & whitney canada corp.
IPC Code(s): F23R3/28, F02C7/22
CPC Code(s): F23R3/286
Abstract: a fuel mixture distribution system for a turbine engine assembly includes a combustor that includes a combustion chamber, a fuel mixture distributor that includes an air conduit defining a mixing chamber between an air inlet and an exit opening to the combustion chamber, and a plurality of fuel passages that are disposed in the air conduit where a fuel flow is introduced and mixed with air in the mixing chamber prior to flowing through the exit opening into the combustion chamber. the air conduit shape is defined to achieve the desired mixing and prevent flashback at all operating conditions.
Inventor(s): Nemanja Ceranic of Mississauga (CA) for pratt & whitney canada corp.
IPC Code(s): F23R3/28, F23R3/14
CPC Code(s): F23R3/286
Abstract: a combustor for a gas turbine engine includes a liner receiving a fuel and air mixing body. the mixing body communicates with a source of fuel, and has an inner chamber centered on a central axis. fuel passages communicate with the source of fuel and deliver fuel into the inner chamber. the inner chamber extends between a bottom wall and an end face leading into a combustion chamber within the liner. inner air swirler passages are formed in the mixing body at an axially intermediate location between the bottom wall and the end wall and deliver air into the inner chamber to mix with fuel from the fuel passages. outer air passages in the mixing body in a portion which is radially outward of the chamber. the outer air passages have a component extending radially inwardly toward the central axis of the chamber.
Inventor(s): Hang Xu of Oakville (CA) for pratt & whitney canada corp.
IPC Code(s): F23R3/28
CPC Code(s): F23R3/286
Abstract: a combustor has a mixing body with a central fuel passage with a central axis and adapted to be connected to source of fuel. a nose at a forward end includes a plurality of fuel injection passages allowing fuel to flow from the central fuel passage into an area forward of an outlet from the fuel injection passages. an inner air supply radially outwardly of the central fuel passage delivers air into inner slots extending downstream of outlets of the fuel injection passages such that air and fuel can begin to be mixed and move downstream of an end of the nose. an outer air supply delivers air downstream of the inner air outlet such that air from the outer air supply, air from the inner slots and fuel from the fuel injection passages are all driven forwardly into a combustion chamber. a gas turbine engine is also disclosed.
Inventor(s): Tin Cheung John Hu of Markham (CA) for pratt & whitney canada corp.
IPC Code(s): F23R3/28, F23D14/82
CPC Code(s): F23R3/286
Abstract: a combustor for a gas turbine engine includes a liner surrounding a fuel and air mixing body. a fuel supply passage communicates into an open fuel plenum downstream of the fuel supply passage. a wall of the mixing body has air openings to receive air flow, and communicate air into mixing passages. the mixing passages pass through the fuel plenum. fuel openings in the mixing passages to allow fuel to flow from the mixing passage and mix with the air. there are passage sections extending downstream of the fuel plenum, such that the mixed air and fuel travels downstream of the fuel plenum and into a combustion chamber. a gas turbine engine is also disclosed.
Inventor(s): Tin Cheung John Hu of Markham (CA) for pratt & whitney canada corp.
IPC Code(s): F23R3/28, F23R3/34
CPC Code(s): F23R3/286
Abstract: a combustor includes a liner and an air fuel mixing body in a wall of the liner. a fuel supply passage provides fuel into the mixing body. the fuel then is injected through radial distribution passages into a mixing plenum. the mixing plenum receives a cellular material. air supply passages deliver air into the mixing plenum. downstream extending passages lead from the mixing plenum to an inner face of the mixing body for delivery of mixed fuel and air into a combustion chamber.
20240263791. HYDROGEN FUEL DISTRIBUTOR_simplified_abstract_(pratt & whitney canada corp.)
Inventor(s): Kian McCaldon of Orangeville (CA) for pratt & whitney canada corp.
IPC Code(s): F23R3/28, F23D14/82, F23R3/04
CPC Code(s): F23R3/286
Abstract: a fuel mixture distribution system for a turbine engine assembly includes a combustor that includes a wall that defines a combustion chamber, a fuel mixture distributor that includes an air conduit that defines a mixing chamber that extends through the wall along between an inlet to an exit opening to the combustion chamber, the air conduit shape is defined to achieve the desired mixing and prevent flashback at all operating conditions, and a fuel distributor extends into the mixing chamber at a location upstream of the exit opening. the fuel distributor includes a plurality of fuel openings where a fuel flow is communicated and mixed with an airflow passing through the mixing chamber.
Inventor(s): Kian McCaldon of Orangeville (CA) for pratt & whitney canada corp.
IPC Code(s): F23R3/28, F02C7/22
CPC Code(s): F23R3/286
Abstract: a fuel nozzle for a turbine engine using hydrogen fuel is provided. the fuel nozzle includes a tubular element, a perforated fuel distributor disposed along the tubular element and comprising a plate body defining holes and a swirler element abuttable with an end wall of a combustor of the turbine engine. the swirler element includes an inner swirler body formed to define a swirl area receptive of hydrogen fuel from the tubular element via the holes and an outer swirler body disposed about the inner swirler body and formed to define openings through which fluid flows radially into the swirl area to mix with the hydrogen fuel prior to flowing into the combustor.
Inventor(s): Tin Cheung John Hu of Markham (CA) for pratt & whitney canada corp.
IPC Code(s): F23R3/28, F23R3/00
CPC Code(s): F23R3/286
Abstract: a combustor includes a liner defining a combustion chamber and receiving a fuel and air mixing body. the mixing body has a central fuel supply, and radial distribution passages communicating fuel from the central fuel supply radially outwardly relative to a central axis of the central fuel supply and to mixing passages. the radial distribution passages have injection ports in the mixing passages. the mixing passages extend from a rear face of the mixing body to an inner face facing into the combustion chamber. air inlets in the mixing body communicate air into the mixing passages, and there is cellular material in the mixing passages at a location at which the fuel is injected into the mixing passages. a gas turbine engine is also disclosed.
Inventor(s): Tin Cheung John Hu of Markham (CA) for pratt & whitney canada corp.
IPC Code(s): F02C3/22, F02C7/232
CPC Code(s): F23R3/286
Abstract: an injector for introducing hydrogen and gas into a combustion chamber of a gas turbine engine includes a convergent-divergent nozzle head and a hydrogen/gas feed nozzle. the convergent-divergent nozzle head is arranged along a nozzle axis and has an upstream end defining an inlet mouth. the hydrogen/gas feed nozzle includes a mixing chamber arranged along the nozzle axis upstream of the inlet mouth, first feed conduits configured to feed hydrogen into the mixing chamber, and second feed conduits configured to feed gas into the mixing chamber. each of the first feed conduits and the second feed conduits are tangentially oriented to the mixing chamber.
Inventor(s): Tin Cheung John Hu of Markham (CA) for pratt & whitney canada corp.
IPC Code(s): F23R3/28, F23D14/58
CPC Code(s): F23R3/286
Abstract: an injector for introducing hydrogen and air into a combustion chamber of a gas turbine engine includes a convergent-divergent nozzle head, a fuel swirler, and a gas swirler. the convergent-divergent nozzle head is arranged along a nozzle axis and has an upstream end that defines an inlet mouth. the swirler head is arranged along the nozzle axis upstream of the inlet mouth and is configured to swirl flow of the hydrogen into the convergent-divergent nozzle head. the gas swirler head is upstream of the inlet mouth and is configured to feed the gas into the convergent-divergent nozzle head.
Inventor(s): Tin Cheung John Hu of Markham (CA) for pratt & whitney canada corp.
IPC Code(s): F23R3/28, F23R3/00
CPC Code(s): F23R3/286
Abstract: a gas turbine engine includes a combustion chamber and groups of injectors for introducing a hydrogen and gas mixture into the combustion chamber. each group of injectors includes radially inner, outer, and intermediate injectors, and each injector includes a hydrogen feed conduit that has an open-cell metallic foam disposed therein.
Inventor(s): Tin Cheung John Hu of Markham (CA) for pratt & whitney canada corp.
IPC Code(s): F23R3/28, F02C7/22
CPC Code(s): F23R3/286
Abstract: a gas turbine engine includes an annular combustion chamber and an injector ring. the annular combustion chamber is disposed about an axis and has first and second axial ends and radially inner and outer walls. the injector ring is disposed about the axis at the first axial end and is configured to introduce a hydrogen and gas mixture into the combustion chamber. the injector ring includes gas feed conduits that open into a central mixing region, a hydrogen manifold cavity that has first and second isolated compartments, first hydrogen feed conduits that extend off of the first isolated compartment and open into the central mixing region, and second hydrogen feed conduits that extend off of the second isolated compartment and open into the central mixing region.
Inventor(s): Jeremy Gonzalez of Montreal (CA) for pratt & whitney canada corp., Jong Park of North York (CA) for pratt & whitney canada corp.
IPC Code(s): G01M3/24
CPC Code(s): G01M3/24
Abstract: a method of and system for inspecting a sealed compartment within a gas turbine engine is provided. the method includes using at least one acoustic transmitter to produce at least one emitted acoustic signal into a compartment interior cavity. the acoustic transmitter is in communication with the at least one port. the array of acoustic sensors is used to sense acoustic signals. the acoustic sensors are disposed in proximity to the seal outside of the interior cavity of the sealed compartment. each acoustic sensor is configured to sense emitted acoustic signals produced by the acoustic transmitter and to produce signal data representative of sensed acoustic signals. the presence or absence of a compromised region of the seal is determined using the signal data from at least one of the acoustic sensors of the array of acoustic sensors.
PRATT & WHITNEY CANADA CORP. patent applications on August 8th, 2024