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公开(公告)号：US12110810B2
公开(公告)日：2024-10-08
申请号：US18158618
申请日：2023-01-24
发明人： Kudum Shinde , Sesha Subramanian , Yashpal Patel
CPC分类号： F01D9/06 , F01D17/105 , F01D17/145 , F02C6/08 , F02C9/18 , F05D2220/323 , F05D2240/14 , F05D2260/232 , F05D2260/605 , F05D2260/606
摘要： A gas turbine engine includes a compressor with an inner casing and an outer casing. The inner casing defines a primary flow path for airflow through the compressor, the inner casing and the outer casing define a bleed air cavity therebetween. The inner casing at least partially defines a first bleed air channel between the primary flow path and the first bleed air cavity. The first bleed air channel is defined between a first wall and a second wall, wherein the first wall is upstream from the second wall. The first wall includes a plurality of holes in fluid communication with the primary flow path and fluidly coupled to a suction manifold. The plurality of holes is configured to energize a fluid boundary layer along the first wall.
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公开(公告)号：US12065937B1
公开(公告)日：2024-08-20
申请号：US18394669
申请日：2023-12-22
申请人： RTX Corporation
CPC分类号： F01D17/14 , B64D27/10 , B64D33/04 , F01D17/16 , F05D2220/323 , F05D2250/90
摘要： A variable area nozzle assembly includes a fixed center plug, a fixed outer nozzle, and an inner nozzle. The fixed center plug includes a plug body and a protrusion. The fixed outer nozzle extends about the fixed center plug. The inner nozzle extends about the fixed center plug. The inner nozzle is disposed between the fixed center plug and the fixed outer nozzle. The inner nozzle forms a primary duct between the inner nozzle and the fixed outer nozzle. The primary duct includes an exit plane. The inner nozzle body forms a secondary duct and a gap. The gap is a nozzle outlet of the secondary duct. The gap includes a gap inlet and a gap outlet. The gap inlet is disposed upstream of the protrusion. The gap outlet is disposed downstream of the protrusion. The inner nozzle body is translatable between a first position and a second position. In the first position, the primary duct has a first area at the exit plane and the inner nozzle body is disposed at the protrusion. In the second position, the primary duct has a second area at the exit plane and the inner nozzle body is spaced from the protrusion.
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公开(公告)号：US20240133312A1
公开(公告)日：2024-04-25
申请号：US18048611
申请日：2022-10-20
发明人： Timothy Unton , Andrew Eifert , Michael Moser
摘要： A vane assembly includes vanes, an actuator assembly, and a controller. The vanes are configured to rotate about their pitch axes. The actuator assembly includes an annular ring arranged radially outward of the vanes and coupled to the vanes, a magnet arranged on the annular ring, and a stator arranged adjacent the magnet. The ring is configured to rotate the vanes about the pitch axes in response to rotation of the ring about the central axis and the stator is configured to selectively rotate the magnet and annular ring about the central axis. The controller controls movement of the ring via the stator and magnets in response to at least one of (i) at least one operating condition of the gas turbine engine, or (ii) at least one operating parameter of the at least one first vane.
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公开(公告)号：US11952943B2
公开(公告)日：2024-04-09
申请号：US18213823
申请日：2023-06-24
发明人： Karan Anand , Hong Yu
CPC分类号： F02C7/042 , F01D17/141 , F02C3/04 , F02C9/20 , F02C9/54
摘要： Assemblies and methods for directing a flow of air through a compressor section of a gas turbine engine are disclosed. A method includes receiving the flow of air over a strut extending radially across a substantially annular gas path of the gas turbine engine, and at least partially confining and modifying a strut wake generated in the flow of air by the strut using one or more variable orientation guide vanes.
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5.发明公开公开(公告)号：US20240076991A1
公开(公告)日：2024-03-07
申请号：US18505595
申请日：2023-11-09
发明人： Ryan C. Humes
CPC分类号： F01D9/023 , F01D17/145 , F23R3/002 , F05D2240/35 , F05D2260/232 , F05D2260/60 , F23R2900/03043
摘要： A gas turbine engine comprises a turbine, a combustor fluidly coupled to the turbine, and a cooling air system. The turbine includes including a turbine rotor having a shaft mounted for rotation about an axis of the gas turbine engine and a set of turbine blades coupled to the turbine rotor for rotation therewith. The combustor includes an outer combustor case and an inner combustor case that cooperate to define a combustion chamber. The cooling air system is configured to cool the turbine using air form the combustion chamber of the combustor.
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公开(公告)号：US11835000B2
公开(公告)日：2023-12-05
申请号：US14972289
申请日：2015-12-17
发明人： Victor Pascu , Anthony C. Jones
CPC分类号： F02C9/18 , F01D17/145 , F02C6/08 , F05D2220/323 , F05D2240/128 , F05D2240/35 , F05D2260/232 , F05D2270/101
摘要： Methods and systems for a gas turbine engine comprising a modulated bleed valve are provided. The gas turbine engine may comprise a turbine nozzle coupled to a controller, a modulated bleed valve in communication with the controller, and a tangible, non-transitory memory providing instructions to the controller to perform operations. The operations may include receiving parameter values from the parameter sensor at various times, determining desired bleed airflows to flow through the modulated bleed valve at various times, and/or commanding the modulated bleed valve to assume an open configuration or a closed configuration at various times. The modulated bleed valve may be configured to allow bleed airflow to bypass a nozzle choke area of the turbine nozzle and join a nozzle airflow.
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公开(公告)号：US11725532B1
公开(公告)日：2023-08-15
申请号：US17804580
申请日：2022-05-30
CPC分类号： F01D17/145 , F01D25/28 , F05D2230/232 , F05D2240/58 , F05D2260/36 , F05D2260/37 , F05D2260/606
摘要： A valve for an air system in an aircraft engine, comprising: a housing defining a chamber having a valve axis circumscribed by a sealing surface; and a piston assembly within the chamber including: a sealing ring; and a body extending annularly about a piston axis collinear with the valve axis, having a first and a second piston surface axially spaced apart, a radially outer piston surface extending axially and located between the first and second piston surfaces, and an annular groove extending radially inwardly from the radially outer piston surface having first and second groove walls spaced apart and axially facing one another, the sealing ring within the annular groove, the body including: a first member defining the first piston surface and the first groove wall; and a second member defining the second piston surface and the second groove wall, the first member and the second member in mating engagement.
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公开(公告)号：US11692459B2
公开(公告)日：2023-07-04
申请号：US17655748
申请日：2022-03-21
发明人： Nicolas Pommier , Mathieu Bissardon , Mathieu Delalandre , Stephane Nicolas Piron , Olivier Renon
CPC分类号： F01D25/24 , F01D17/145 , F01D25/162 , F01D25/30 , F02C6/08 , F02C7/32 , F05D2220/30 , F05D2230/10 , F05D2230/232 , F05D2230/60 , Y02T50/60
摘要： A method for manufacturing a turbine engine part in which a first rough casting element includes a first face and a second face opposite to each other is assembled by the second face on an orifice which has a second element of the part. The method includes machining a through-cavity in the first element which opens at the first face and from the second face of the first element and machining the first face of the first element so as to form an area suitable for ensuring the attachment of a conduit on the first element. The machining of the cavity and of the first face is achieved by using a machining reference frame based on the second element.
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公开(公告)号：US11668206B1
公开(公告)日：2023-06-06
申请号：US17654142
申请日：2022-03-09
发明人： Kyle Safford , Kyle Benson , Mithun Raj K K , Radu I. Danescu , Richard W. Johnson , Joseph M. Harvey , Brian P. Hansen
CPC分类号： F01D21/12 , F01D17/145 , F01D21/003 , F01D25/14 , F01D25/26 , F05D2260/232 , F05D2260/60 , F05D2270/303 , F05D2270/3013 , F05D2270/80
摘要： This application provides a temperature gradient control system for a double wall casing of a compressor. The double wall casing may include an inner casing and an outer casing such that a flow of air is pulled through the double wall casing. The temperature gradient control system may include upper discharge piping with an upper modulation valve and a lower discharge piping with a lower modulation valve. The upper modulation valve and/or the lower modulation valve modulate the flow air pulled through the double wall casing to reduce a temperature gradient across the outer casing.
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公开(公告)号：US11661887B2
公开(公告)日：2023-05-30
申请号：US17319439
申请日：2021-05-13
CPC分类号： F02C7/045 , F02C7/042 , B64D2033/0206 , B64D2033/0286 , F01D17/143 , F02K3/025 , F02K3/04 , F02K3/06 , F02K3/068 , F05D2250/311 , F05D2250/712 , F05D2250/90 , F05D2260/96
摘要： A variable geometry inlet system of an aircraft engine includes an inlet duct. The inlet duct includes at least first and second sections moveable between extended and retracted positions such that the inlet duct defines a variable axial length of an inlet passage for selective flight conditions. The inclusion of acoustic treatment may assist in controlling noise.
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