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1.发明授权
公开(公告)号：EP3208425B1
公开(公告)日：2019-09-11
申请号：EP17160228.7
申请日：2012-05-24
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公开(公告)号：EP3486496A1
公开(公告)日：2019-05-22
申请号：EP18207631.5
申请日：2018-11-21
发明人： VOYTOVYCH, Dmytro Mykolayovych , STAROSELSKY, Alexander , SHARMA, Om P. , SUCIU, Gabriel L. , MERRY, Brian , ALVANOS, Ioannis
摘要： The present invention relates to a shrouded fan for gas turbine engines, in particular for a boundary ingestion engine, wherein the fan (200) includes a hub (210), a plurality of blade bodies (220) extending radially outward from the hub (210) to a first partial shroud (230) and a plurality of blade tips (240, 240') extending radially outward from the partial shroud (230). The partial shroud (230) is arranged such as to be at an intersection with a boundary layer of the aircraft's fuselage, thus, counteracting unsteady loading by varying the blade-pitch-ratio. The fan (200) may additionally comprise an outer shroud (250) as well as a second partial span shroud (432). The quantity of blade tips (240) is higher than the quantity of blade bodies (220), allowing greater granularity control over amount of fluid ingested at any given radial position.
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公开(公告)号：EP2841339B1
公开(公告)日：2019-01-23
申请号：EP13781678.1
申请日：2013-02-07
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公开(公告)号：EP3358174A1
公开(公告)日：2018-08-08
申请号：EP18155402.3
申请日：2018-02-06
CPC分类号： F01D25/30 , F01D9/02 , F02C3/04 , F02K1/04 , F02K1/48 , F02K3/06 , F05D2240/14 , F05D2260/96 , F05D2300/6033 , Y02T50/672
摘要： A turbine exhaust assembly (70) for a gas turbine engine (20) includes a turbine exhaust case (72) comprised of CMC material and attachable to a turbine case (74), a tail cone (76) comprised of CMC material that has a leading edge (76L) and a trailing edge (76T), and an exhaust mixer (80) comprised of CMC material and coupled to the turbine exhaust case (72). The exhaust mixer (80) has a plurality of lobes (86) arranged about the tail cone (76) to define an exhaust flow path (E). A plurality of struts (78) extend from the tail cone (76) to support the exhaust mixer (80) at a location aft of the leading edge (86L) of the tail cone (76).
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公开(公告)号：EP2820254B1
公开(公告)日：2018-05-02
申请号：EP13754626.3
申请日：2013-02-11
CPC分类号： F02C7/185 , F01D5/081 , F01D25/125 , F02C6/08 , F02C7/06 , F05D2220/32 , F05D2260/232
摘要： A gas turbine engine includes a heat exchanger, a bearing compartment, and a nozzle assembly in fluid communication with the bearing compartment. The heat exchanger exchanges heat with a bleed airflow to provide a conditioned airflow. The bearing compartment is in fluid communication with the heat exchanger. A first passageway communicates the conditioned airflow from the heat exchanger to the bearing compartment. A second passageway communicates the conditioned airflow from the bearing compartment to the nozzle assembly.
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公开(公告)号：EP3080401A1
公开(公告)日：2016-10-19
申请号：EP14859735.4
申请日：2014-11-05
CPC分类号： F01D5/147 , F01D5/18 , F01D5/282 , F01D5/284 , F01D5/326 , F02C3/04 , F02C7/12 , F05D2220/32 , F05D2230/236 , F05D2230/51 , F05D2240/11 , F05D2240/12 , F05D2300/6033 , Y02T50/672
摘要： An airfoil component includes a first segment that has a first piece of a mount and a first piece of an airfoil. The first segment is formed of a first ceramic-based material. A second segment includes a second piece of the mount and a second piece of the airfoil. The second segment is formed of a second ceramic-based material. The first and second segments are bonded together along a bond joint such that the first and second pieces of the mount are bonded to each other and the first and second pieces of the airfoil are bonded to each other.
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公开(公告)号：EP2776682A2
公开(公告)日：2014-09-17
申请号：EP12852467.5
申请日：2012-11-09
CPC分类号： F01D11/001 , F01D11/122 , F01D11/127 , F05D2230/64 , F05D2250/184 , F05D2260/38
摘要： A seal for sealing a rotor of a rotary machine to a stator thereof which circumscribes the rotor and is separated therefrom by a gap comprises a nonrotational sealing element received within an annular slot in the stator and radially translatable with respect thereto, and extending into the gap for sealing to rotational sealing element carried by the rotor. A resilient biasing element received between the nonrotational sealing element and a floor of the slot biases the nonrotational sealing element radially inwardly toward the rotational sealing element and limits radially outward movement of the nonrotational sealing element. A guide extending into said gap from the slot engages the nonrotational sealing element to prevent axial misalignment thereof with the machine's rotor.
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9.发明公开
公开(公告)号：EP3640434A3
公开(公告)日：2020-07-29
申请号：EP19196577.1
申请日：2012-05-24
摘要： A Ceramic Matrix Composite (CMC) platform for an airfoil (66C) of a gas turbine engine (20) includes a CMC platform segment (86,88) which at least partially defines an airfoil profile.
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