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公开(公告)号：US20240060428A1
公开(公告)日：2024-02-22
申请号：US17892777
申请日：2022-08-22
发明人： Peter BOYD , Andrew GHATTAS
CPC分类号： F01D21/003 , G01M15/14 , F05D2220/323 , F05D2260/80 , F05D2260/83
摘要： Health monitoring systems and associated methods for gas turbine engines are provided. A health monitoring method includes using a microphone to acquire operation data indicative of acoustic energy generated in a core gas path of the gas turbine engine. The operation data is compared to reference data indicative of an acoustic signature of fluid noise associated with a non-normal condition in the core gas path of the gas turbine engine. Based on the comparing of the operation data to the reference data, the non-normal condition is determined to exist within the core gas path of the gas turbine engine. A signal indicative of the existence of the non-normal condition within the core gas path of the gas turbine engine is output.
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公开(公告)号：US11906017B1
公开(公告)日：2024-02-20
申请号：US18327945
申请日：2023-06-02
CPC分类号： F16H1/28 , F02C7/36 , F16D3/06 , F16H57/043 , F16H57/0456 , F16H57/0471 , F16H57/0486 , F05D2260/40311 , F16D2250/0084 , F16D2300/12
摘要： The torque transfer assembly can have a torque shaft rotatable around a rotation axis, the torque shaft having a first end and a second end opposite the first end along the rotation axis, a first reference feature at an intermediary location between the first end and the second end, and a sun gear integrated to the torque shaft, at the first end, the second end has a first external diameter, and the sun gear having a second external diameter greater than the first external diameter; and a reference tube having a fixed end secured to the torque shaft adjacent the second end, a free end having a second reference feature adjacent the first reference feature, the reference tube extending around the torque shaft, the reference tube having an internal diameter, the internal diameter being between the first external diameter and the second external diameter.
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公开(公告)号：US20240052852A1
公开(公告)日：2024-02-15
申请号：US17884167
申请日：2022-08-09
发明人： Jason Nichols , David Batch , Daniel Poick
CPC分类号： F04D29/563 , F04D29/547 , F05D2240/12
摘要： A gas turbine engine apparatus includes an engine flowpath, a protuberance and a variable vane. The protuberance projects into the engine flowpath. The variable vane extends across the engine flowpath. The variable vane includes a pivot axis and an airfoil. The variable vane is configured to pivot about the pivot axis between a first position and a second position. The airfoil extends spanwise along a span line between a first end and a second end. The airfoil extends chordwise along a chord line between a leading edge and a trailing edge. A recess extends spanwise into the airfoil from the first end. The airfoil, at the first end, is spaced from the protuberance when the variable vane is in the first position. The airfoil, at the first end, is aligned with the protuberance and the protuberance projects into the recess when the variable vane is in the second position.
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公开(公告)号：US20240052758A1
公开(公告)日：2024-02-15
申请号：US17884201
申请日：2022-08-09
发明人： Philippe Savard , Guy Lefebvre
CPC分类号： F01D25/24 , F01D9/041 , F05D2240/14
摘要： An assembly is provided for a gas turbine engine. This engine assembly includes a bladed rotor rotatable about an axis, and an engine case. The engine case includes an outer duct wall, a first circumferential stiffener, a second circumferential stiffener and a plurality of axial stiffeners. The outer duct wall forms a shroud around the bladed rotor. The first circumferential stiffener extends circumferentially about the outer duct wall. The second circumferential stiffener extends circumferentially about the outer duct wall. The axial stiffeners are arranged circumferentially about the outer duct wall. Each of the axial stiffeners extends axially between the first circumferential stiffener and the second circumferential stiffener.
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公开(公告)号：US11898503B2
公开(公告)日：2024-02-13
申请号：US18070728
申请日：2022-11-29
发明人： Yves Cloutier
IPC分类号： F02C9/28
CPC分类号： F02C9/28 , F05D2240/35 , F05D2270/301 , F05D2270/303
摘要： Methods and systems for determining an engine temperature for a gas turbine engine are provided. An estimated combustor temperature is determined based on at least one operating condition of the gas turbine engine and an estimated vane mass flow. A corrected vane mass flow is determined based on the estimated combustor temperature, the estimated vane mass flow, and a combustor pressure. The corrected vane mass flow is compared to a reference vane mass flow to obtain the mass flow correction factor. When a condition associated with the mass flow correction factor is not satisfied, the estimated combustor temperature is adjusted based on the mass flow correction factor to produce an adjusted combustor temperature; and the mass flow correction factor is updated based on the adjusted combustor temperature. When the condition associated with the mass flow correction factor is satisfied, the estimated combustor temperature is assigned as the engine temperature.
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公开(公告)号：US11891906B2
公开(公告)日：2024-02-06
申请号：US17651913
申请日：2022-02-22
发明人： Maciej Piotrowski , Lukasz Pokrzywa
IPC分类号： F01D25/18 , F16C33/66 , F01D25/16 , F16F15/023
CPC分类号： F01D25/18 , F01D25/162 , F16C33/6685 , F16F15/0237 , F16C2360/23
摘要： A bearing housing for a bearing having an outer race, the bearing housing comprising: an annular wall extending about an axis and axially between a first end and a second end, the annular wall including: a plurality of holes spaced circumferentially from one another and spaced axially from the first end, the plurality of holes extending through the annular wall toward the axis; and an interior housing surface extending about the axis and defining interior openings of the plurality of holes, the interior housing surface having a cylindrical portion defining a seat for radial engagement with the outer race, the cylindrical portion extending axially from a first location proximate to the first end to at least a second location between the first location and the interior openings.
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公开(公告)号：US11885242B2
公开(公告)日：2024-01-30
申请号：US17662143
申请日：2022-05-05
发明人： Hervé Turcotte , Kenneth Parkman , Oleg Morenko , Nicholas Guglielmin , Gavin Kisun , Ryan Miskie
CPC分类号： F01D9/065 , F01D25/162 , F05D2220/323 , F05D2240/12 , F05D2240/53 , F05D2260/60
摘要： An aircraft engine has: a compressor section having a compressor rotor rotatable about a central axis; a diffuser downstream of the compressor rotor, the diffuser including a diffuser ring extending circumferentially around the central axis; a bearing housing secured to the diffuser ring, the bearing housing contained within a volume located radially inwardly of the diffuser ring; and an air manifold secured to the diffuser ring, the air manifold defining inlets in fluid flow communication with the compressor section and an outlet in fluid flow communication with the volume.
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公开(公告)号：US11883882B2
公开(公告)日：2024-01-30
申请号：US17381483
申请日：2021-07-21
IPC分类号： B22F3/22 , B22F3/10 , B22F7/02 , B22F7/06 , F01D9/04 , F01D25/24 , B22F3/105 , B22F5/00 , B22F3/02
CPC分类号： B22F3/225 , B22F3/105 , B22F3/1021 , B22F5/009 , B22F7/02 , B22F7/06 , F01D9/04 , F01D25/246 , B22F3/02 , B22F2003/023 , B22F2999/00 , F05D2230/22 , B22F2999/00 , B22F2003/023 , B22F3/225 , B22F2207/01
摘要： A method of forming a component from a part in the green state, including selecting at least one first portion of the part to undergo a different local volume reduction from at least one second portion to obtain the component. The green part is provided with the first portion(s) having a first solid loading and the second portion(s) having a second solid loading different from the first solid loading, then debound and sintered to obtain the component. The different first and second solid loadings produce the different local volume reduction in the first portion(s). The first portion(s) can be selected by determining a resulting final shape obtained from debinding and sintering a green part having a uniform first volumetric proportion of binder, and selecting the first portion(s) requiring a different local deformation than that producing the resulting final shape to obtain a desired final shape.
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公开(公告)号：US11879384B2
公开(公告)日：2024-01-23
申请号：US18107758
申请日：2023-02-09
发明人： Sean Durand
摘要： Methods and systems of starting a gas turbine engine are provided. During startup, a fuel pressure associated with a primary fuel supply of the gas turbine engine is monitored. A low-pressure event for the primary fuel supply is detected when the fuel pressure falls below a predetermined threshold. Responsive to detecting the low pressure event, an electric backup boost pump is activated by an engine controller to provide fuel to the gas turbine engine.
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公开(公告)号：US11874196B2
公开(公告)日：2024-01-16
申请号：US17822148
申请日：2022-08-25
发明人： Douglas Monahan , Gabor Kafka
摘要： A portable attitude test stand (PATS) for an aircraft engine, has: a support frame mountable on a trailer of a road vehicle; a test cell supported by the support frame and sized to receive the aircraft engine, the test cell operable to rotate the aircraft engine about a pitch axis and a roll axis of the aircraft engine; and an actuator operatively connected to the test cell and to the support frame, the actuator operable to lower and raise the test cell relative to the support frame between a transport configuration in which the test cell has a transport height and a test configuration in which the test cell has a test height, the test height being greater than the transport height.
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