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公开(公告)号：US11879342B2
公开(公告)日：2024-01-23
申请号：US17912664
申请日：2021-03-19
发明人： Aurélien Gaillard , Clément Emile André Cazin , Clément Jarrossay , Pascal Cédric Tabarin , Nicolas Paul Tableau
CPC分类号： F01D11/24 , F01D5/186 , F01D25/12 , F01D25/24 , F05D2220/32 , F05D2240/14 , F05D2240/30 , F05D2240/55 , F05D2260/202
摘要： A turbine assembly (1) comprising: —a plurality of turbine ring sectors (20) made of ceramic-matrix composite material, —a ring support structure (3), comprising an annular shroud (6), and in addition —a plurality of angular spacer sectors (70) together forming an annular spacer (7), said annular spacer (7) being, on the one hand, fixed to the turbine ring (2) and, on the other hand, fixed to said annular shroud (6), characterized in that said turbine assembly (1) comprises at least one air diffuser (8), which is configured to diffuse cooling air onto the radially outer face (212) of at least one of said turbine ring sectors (20), and in that said at least one air diffuser (8) is mounted by being nested on one of said angular spacer sectors (70), in a nested position.
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公开(公告)号：US20230407757A1
公开(公告)日：2023-12-21
申请号：US17843113
申请日：2022-06-17
发明人： Dean Johnson , Thomas E. Clark
CPC分类号： F01D11/125 , F05D2240/55 , F05D2300/6033 , F01D11/24
摘要： A seal system for a gas turbine engine includes a ceramic matrix composite (CMC) seal arc segment and a carrier supporting the CMC seal arc segment. The CMC seal arc segment defines radially inner and outer sides and has an abradable layer disposed on the radially outer side. There is a cooling cavity radially between the carrier and the abradable layer. The carrier includes a ridge that projects into a groove in the abradable layer and provides a labyrinth seal that partitions the cooling cavity into sub-cavities.
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公开(公告)号：US11639668B2
公开(公告)日：2023-05-02
申请号：US16976218
申请日：2019-02-26
摘要： A method for controlling the clearance between the blade tips of a high-pressure turbine of a gas turbine aircraft engine and a turbine shroud, including the controlling of a valve delivering a stream of air to the turbine shroud, this method further including the following steps: the detection of a transient acceleration phase of the engine; the receiving of an item of data representative of the gas temperature at the outlet of the combustion chamber of the engine; a valve opening command, to deliver the air stream to the turbine shroud or to increase the flow rate of the delivered air stream, if the transient acceleration phase is detected and if the gas temperature at the outlet of the combustion chamber is greater than a first temperature threshold corresponding to a degraded clearance characteristic of an aged engine, this threshold being less than an operating limit temperature of the engine.
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公开(公告)号：US20230116425A1
公开(公告)日：2023-04-13
申请号：US17913310
申请日：2021-03-22
发明人： Clément JARROSSAY , Sébastien Serge Francis CONGRATEL , Antoine Claude Michel Etienne DANIS , Aurélien GAILLARD , Nicolas Paul TABLEAU
摘要： Turbine shroud assembly comprising sections (10) made from CMC and forming a shroud (1) and a support structure (3), each section having a base (12) with a radially internal face (12a) and a radially external face (12b), from which there extend in a projecting manner an upstream attachment lug (14) and a downstream attachment lug (16), the support structure comprising a collar (31), from which there radially extend in a projecting manner towards the shroud an upstream radial flange (32) and a downstream radial flange (36), by which the lugs of each section of the shroud are retained, the shroud (1) being retained by axial pins (119, 120) which cooperate, on the one hand, with the upstream radial flange, via first and second annular end plates (33, 34), and directly with the downstream radial flange and, on the other hand, with the upstream and downstream attachment lugs, respectively.
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公开(公告)号：US20230035302A1
公开(公告)日：2023-02-02
申请号：US17388228
申请日：2021-07-29
发明人： Travis J. Packer , James Hamilton Grooms , David Fasig , Richard William Jendrix , Scott Alan Schimmels , Bradford Alan Tracey , Michael Alan Hile , Thomas Ryan Wallace
摘要： A clearance control assembly for a gas turbine engine that defines an axial direction and a radial direction and includes a stage of rotor blades and a shroud hanger. The assembly includes a case configured to be positioned outward along the radial direction from the stage of rotor blades when installed in the gas turbine engine. The case is further configured to be engaged with the shroud hanger at a first location when installed in the gas turbine engine. The assembly also includes a baffle positioned outward along the radial direction from the case to define a chamber therebetween. The baffle has a forward end and an aft end. The forward end of the baffle is engaged with the case to form a first seal and the aft end of the baffle is engaged with the case to form a second seal. The baffle, the case, or both define an inlet to allow a fluid to enter the chamber and the case defines an outlet to allow the fluid to exit the chamber.
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公开(公告)号：US11371378B2
公开(公告)日：2022-06-28
申请号：US17204947
申请日：2021-03-18
发明人： Seung Min Lee , Yong Hwan Kwon , Dong II Kim , Jin Woong Ha
摘要： An apparatus for controlling tip clearance between a turbine casing and a turbine blade is provided. The apparatus for controlling tip clearance includes a casing surrounding the turbine blade, a cooling plate installed in a groove, formed in a circumferential direction in the casing, and contracted by cold air supplied thereto, the cooling plate having at least one fin formed on an outer peripheral surface thereof, and a ring segment mounted radially inside the cooling plate.
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公开(公告)号：US11293639B2
公开(公告)日：2022-04-05
申请号：US16766016
申请日：2018-11-01
发明人： Andrea Viano
摘要： A heat shield for a gas turbine engine has a main body having a first and second surface, the first surface exposed to a hot working gas, a plurality of walls upstanding from the second surface and an impingement plate. The impingement plate is on top of at least one wall and forms a chamber and has an array of impingement holes. At least one pair of divider walls are formed within the chamber and extend between the impingement plate and the second surface. The first divider wall extends from a first wall towards a second wall, the second divider wall extends from the second wall towards the first wall. The first and second divider walls both extend such that there is no clear line of sight in a perpendicular direction to the first divider wall and/or second divider wall and are spaced apart with respect to the perpendicular direction.
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公开(公告)号：US11242766B2
公开(公告)日：2022-02-08
申请号：US16768221
申请日：2018-11-28
发明人： Benjamin Boudsocq
摘要： The invention relates to a method for measuring the flow rate of cooling air in a cooling air circuit (13) of a casing (121) of a high-pressure turbine (9) of a turbomachine (1). The invention is characterized in that sensors (21, 22, 24, 26, 28) are used to measure a total pressure at the fan inlet, a static pressure at the outlet of the high-pressure compressor (6), a rotational speed of the low-pressure shaft (101), a rotational speed of the high-pressure shaft (91) and a degree of valve opening of the cooling air circuit (13), a calculation unit is used to calculate the flow rate of cooling air on the basis of at least the measurement of these.
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公开(公告)号：US20210404348A1
公开(公告)日：2021-12-30
申请号：US17307262
申请日：2021-05-04
申请人： GE Avio S.r.l.
摘要： Aspects of the disclosure generally relate to a turbine engine and method of operating, wherein a change in sealing status can be determined within a cavity between an outer casing and a rotor within the turbine engine. Aspects of the disclosure further relate to a supply of air to the cavity within the turbine engine.
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公开(公告)号：US11174745B2
公开(公告)日：2021-11-16
申请号：US16662203
申请日：2019-10-24
发明人： Asako Inomata , Shinji Tanigawa , Iwataro Sato , Hideyuki Maeda , Satoru Sekine , Kazutaka Tsuruta
摘要： A stator blade of an embodiment includes: a blade effective part having hollow portions; an outer shroud having an outer plate flange portion provided on a radial-direction outer side of the blade effective part, and a pair of outer mounting portions provided in a circumferential direction on a front edge side and a rear edge side; an inner shroud having an inner plate flange portion provided on a radial-direction inner side of the blade effective part; cooling medium introduction passages which introduce a cooling medium via opening portions formed in the outer plate flange portion and passing through the outer plate flange portion in a radial direction, to the hollow portions; and a cooling medium introduction passage formed in a direction along a surface of the outer plate flange portion in a wall thickness of the outer plate flange portion, which introduces a cooling medium to the hollow portion.
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