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1.发明公开公开(公告)号：US20240280031A1
公开(公告)日：2024-08-22
申请号：US18614048
申请日：2024-03-22
CPC分类号： F01D11/18 , F01D11/001 , F01D9/041 , F01D11/005 , F01D11/025 , F01D11/08 , F01D25/246 , F01D25/26 , F05D2220/32 , F05D2230/642 , F05D2240/11 , F05D2240/30 , F05D2240/55
摘要： A gas (or steam) turbine is disclosed including: a rotor with at least one array of rotor blades, a stator with a casing and a shroud ring; the shroud ring extends around the array of blades rotor and the casing extends around the shroud ring. The shroud ring has radial size independent from temperature thanks to its material, and is movably coupled with the casing so to allow the casing of the stator to thermally expand and contract during operation of the turbine while maintaining the shroud ring radial size. Also the rotor thermally expands and contracts during operation of the turbine, and, at working temperature, tip regions of the rotor blades are in close proximity to an inner region of the shroud ring so that clearance is small or even zero at working condition.
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公开(公告)号：US12037912B2
公开(公告)日：2024-07-16
申请号：US17842932
申请日：2022-06-17
申请人： RTX Corporation
发明人： Paul M. Lutjen , John R. Farris , Matthew A. Devore , John A. Sharon , James F. Wiedenhoefer , Mario P. Bochiechio , Brian T. Hazel
CPC分类号： F01D11/18 , F01D25/005 , F05D2230/22 , F05D2230/90 , F05D2260/30
摘要： An advanced passive clearance control (APCC) control ring is provided. The APCC control ring includes first and second cover sections, first and second wall sections and a control ring. At least one of the first and second cover sections is bonded to corresponding edges of the first and second wall sections by field assisted sintering technology (FAST) processing along a bond surface to form an enclosure for the control ring.
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公开(公告)号：US20240218803A1
公开(公告)日：2024-07-04
申请号：US18594065
申请日：2024-03-04
发明人： Bhaskar Nanda Mondal , John Joseph Rahaim , Thomas Moniz , Steven A. Ross , Joel Kirk , Scott Hunter , Daniel Fusinato
CPC分类号： F01D11/18 , F01D11/025 , F01D25/005 , F05D2240/11 , F05D2240/55 , F05D2260/30 , F05D2300/5021 , F05D2300/6033 , Y02T50/60
摘要： A passive clearance control limits thermal expansion between stator components relative to rotor components. A control ring controls clearance in a passive manner and is located on or adjacent to stationary components which thermally expand during engine operation. The control ring is formed of material having low coefficient of thermal expansion such as CMCs (Ceramic Matrix Composites) and therefore limits, inhibits or restrains expansion of the adjacent stator components as temperatures increase. Limiting expansion of the stator component reduces rotor/stator clearances and limits parasitic leakage of fluid along the flow path through the engine core.
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公开(公告)号：US11788425B2
公开(公告)日：2023-10-17
申请号：US17561156
申请日：2021-12-23
申请人： General Electric Company , General Electric Deutschland Holding GmbH , General Electric Company Polska Sp. z o.o.
发明人： Ashish Sharma , Piotr Jerzy Kulinski , Adam Tomasz Pazinski , Tomasz Jan Bulsiewicz , Scott Alan Schimmels
CPC分类号： F01D11/18 , F01D9/04 , F01D11/24 , F01D25/24 , F01D25/246 , F05D2220/32 , F05D2260/201
摘要： A gas turbine engine including: a first turbine rotor assembly including a plurality of first turbine rotor blades extended within a gas flowpath; and a casing surrounding the first turbine rotor assembly, wherein the casing comprises an outer casing wall extended around the first turbine rotor assembly; a plurality of vanes extended from the outer casing wall and within the gas flowpath at a location aft of the first turbine rotor assembly; and a thermal control ring positioned outward along a radial direction from the outer casing wall, and wherein the thermal control ring comprises a body and a plurality of pins, and wherein the plurality of pins extend between the outer casing wall and the body.
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公开(公告)号：US20230044147A1
公开(公告)日：2023-02-09
申请号：US17395882
申请日：2021-08-06
发明人： Simon Baker-Ostiguy
IPC分类号： F01D11/18
摘要： An assembly is provided for a turbine engine. This assembly includes a static structure and an impeller rotor housed within the static structure. The impeller rotor includes a vane structure and a shroud. The vane structure includes a first sidewall, a second sidewall and a plurality of vanes arranged circumferentially about a rotational axis. The vanes include a first vane. The first vane includes a first portion, a second portion and a third portion. The first portion is axially between the first sidewall and the second sidewall. The second portion is radially between the first sidewall and the shroud. The third portion is radially between the second sidewall and the shroud. The shroud circumscribes the vane structure. A gap is formed by and extends between the shroud and the static structure. A dimension of the gap changes as the gap extends along the shroud.
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公开(公告)号：US20220349316A1
公开(公告)日：2022-11-03
申请号：US17864534
申请日：2022-07-14
发明人： Bhaskar Nanda Mondal , John Joseph Rahaim , Thomas Moniz , Steven A. Ross , Joel Kirk , Scott Hunter , Daniel Fusinato
摘要： A passive clearance control limits thermal expansion between stator components relative to rotor components. A control ring controls clearance in a passive manner and is located on or adjacent to stationary components which thermally expand during engine operation. The control ring is formed of material having low coefficient of thermal expansion such as CMCs (Ceramic Matrix Composites) and therefore limits, inhibits or restrains expansion of the adjacent stator components as temperatures increase. Limiting expansion of the stator component reduces rotor/stator clearances and limits parasitic leakage of fluid along the flow path through the engine core.
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公开(公告)号：US11434785B2
公开(公告)日：2022-09-06
申请号：US16453232
申请日：2019-06-26
申请人： MTU Aero Engines AG
发明人： Manfred Feldmann
摘要： A jacket ring assembly for a turbomachine, the jacket ring assembly including a casing part, a jacket ring segment which is adapted to radially outwardly surround a rotor blade ring and to this end is disposed radially inwardly of the casing part, as considered with respect to a longitudinal axis of the turbomachine, and a segmented ring which is circumferentially divided into segments and by which the jacket ring segment is mounted to the casing part, the segmented ring being axially form-fittingly disposed on a form-fitting element of the casing part, for which purpose each of the respective segments of the segmented ring is radially outwardly assembled with the form-fitting element, and the segmented ring forming a supporting seat on which the jacket ring segment is seated and radially inwardly supported with an axially forward end.
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公开(公告)号：US20220213802A1
公开(公告)日：2022-07-07
申请号：US17142357
申请日：2021-01-06
发明人： Steven Douglas Johnson , Julius John Montgomery , Brandon Wayne Miller , Robert Proctor , Bradley W. Fintel , Jeffrey Douglas Rambo
摘要： A system for controlling blade clearances within a gas turbine engine includes a rotor disk and a rotor blade coupled to the rotor disk. Additionally, the system includes an outer turbine component positioned outward of the rotor blade such that a clearance is defined between the rotor blade and the outer turbine component. Furthermore, the system includes a heat exchanger configured to receive a flow of cooling air bled from the gas turbine engine and transfer heat from the received flow of the cooling air to a flow of coolant to generate cooled cooling air. Moreover, the system includes a valve configured to control the flow of the coolant to the heat exchanger. In this respect, the cooled cooling air is supplied to at least one of the rotor disk or the rotor blade to adjust the clearance between the rotor blade and the outer turbine component.
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公开(公告)号：US20220090511A1
公开(公告)日：2022-03-24
申请号：US17398187
申请日：2021-08-10
摘要： The present technique presents a blade 1 for a gas turbine 10. The blade 1 includes an airfoil 100 having an airfoil tip part 100a and a pressure side 102 and a suction side 104 meeting at a leading edge 106 and a trailing edge 108 and defining an internal space 100s of the airfoil 100. A squealer tip 80, 90 is arranged at the airfoil tip part 100a. The squealer tip 80, 90 comprises a suction side rail 90. The suction side rail 90 comprises a chamfer part 90x and at least one squealer tip cooling hole 99. The chamfer part 90x comprises a chamfer surface 9. An outlet 99a of the at least one squealer tip cooling hole 99 is disposed at the chamfer surface 9.
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10.发明授权公开(公告)号：US11105338B2
公开(公告)日：2021-08-31
申请号：US16579011
申请日：2019-09-23
发明人： Michael Nesteroff , Jonathan Acker , Jeffrey Crutchfield , Nate Cooper , Mark Whitlock , Nathan Ottow
IPC分类号： F04D29/42 , F04D29/16 , F01D5/04 , F01D11/22 , F04D17/02 , F04D17/10 , F02C3/08 , F04D27/02 , F01D11/08 , F04D29/62 , F01D11/18
摘要： A system for controlling the clearance distance between an impeller blade tip of a centrifugal compressor and a radially inner surface of an impeller shroud in a turbine engine. The system comprises a high pressure air source, an air piston mounted between an engine casing and the shroud and adapted to receive high pressure air from the high pressure air source, a mounting arm coupling the shroud and air piston, and a slidable coupling adapted to allow axial movement of the shroud and joining the shroud to an axial member.
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