-
公开(公告)号：US20240318571A1
公开(公告)日：2024-09-26
申请号：US18357374
申请日：2023-07-24
CPC分类号： F01D11/025 , F01D11/08 , F16J15/442
摘要： A turbine engine is provided. The gas turbine engine defines a radial direction, and includes: a rotor; a stator comprising a carrier; a seal assembly disposed between the rotor and the stator, the seal assembly comprising a seal segment having a seal face forming a fluid bearing with the rotor; and a seal support assembly comprising a torsional spring extension extending from the carrier, from the seal segment, or both, to bias the seal segment along the radial direction.
-
公开(公告)号：US20240318570A1
公开(公告)日：2024-09-26
申请号：US18189379
申请日：2023-03-24
发明人： Ravindra Shankar Ganiger , David Raju Yamarthi , Chandrashekhar Kandukuri , Deepak Trivedi , Narendra Anand Hardikar , Vidyashankar Ramasastry Buravalla , Steven Douglas Johnson , Amit Goyal , Grant Robert Portune , Himanshu Gupta , Srinivasan Swaminathan , Shalini Thimmegowda , Guru Venkata Dattu Jonnalagadda , Shalabh Saxena , Prateek Jalan
IPC分类号： F01D11/02
CPC分类号： F01D11/025 , F05D2240/53 , F05D2240/55 , F05D2260/38
摘要： A turbine engine is provided. The turbine engine defines an axial direction and a radial direction, and includes: a rotor; a stator comprising a carrier; a seal assembly disposed between the rotor and the stator, the seal assembly defining a high-pressure side and a low-pressure side and comprising a plurality of seal segments, the plurality of seal segments including a seal segment having a seal face forming a fluid bearing with the rotor, a lip, and a body, the lip extending from the body along the axial direction of the turbine engine on the high-pressure side and including an outer pressurization surface along the radial direction of the turbine engine; and a seal support assembly, the seal support assembly comprising a spring arrangement extending between the carrier and the first seal segment to counter a pressure on the outer pressurization surface during operation of the turbine engine.
-
公开(公告)号：US20230296028A1
公开(公告)日：2023-09-21
申请号：US18311443
申请日：2023-05-03
发明人： Ross Wilson , John R. Farris , Michael G. McCaffrey , Theodore W. Hall , John J. Korzendorfer , Elizabeth F. Vinson , Jeffrey Michael Jacques , John E. Paul , Edwin Otero , Alan W. Stoner
CPC分类号： F01D11/02 , F01D11/025 , F01D25/04 , F16F15/06 , F16J15/44 , F16J15/442 , F05D2220/32 , F05D2240/55 , F05D2260/96 , F05D2300/171
摘要： A method of damping vibrations in a seal includes inserting a first wave spring between a first beam and a second beam of the seal. The seal can be for a gas turbine engine and can include a full hoop outer ring, a shoe coupled to the full hoop outer ring via the first beam (e.g., an outer beam) and the second beam (e.g., an inner beam), and the first wave spring in contact with the first beam and the second beam.
-
公开(公告)号：US11674401B2
公开(公告)日：2023-06-13
申请号：US15931434
申请日：2020-05-13
发明人： Ross Wilson , John R. Farris , Michael G. McCaffrey , Theodore W. Hall , John J. Korzendorfer , Elizabeth F. Vinson , Jeffrey Michael Jacques , John E. Paul , Edwin Otero , Alan W. Stoner
CPC分类号： F01D11/02 , F01D11/025 , F01D25/04 , F16F15/06 , F16J15/44 , F16J15/442 , F05D2220/32 , F05D2240/55 , F05D2260/96 , F05D2300/171
摘要： A seal for a gas turbine engine includes a full hoop outer ring, a shoe coupled to the full hoop outer ring via an inner beam and an outer beam, and a wave spring in contact with at least one of the inner beam or the outer beam.
-
公开(公告)号：US20190085711A1
公开(公告)日：2019-03-21
申请号：US15709617
申请日：2017-09-20
CPC分类号： F01D11/06 , F01D1/26 , F01D5/03 , F01D5/225 , F01D11/025 , F01D11/14 , F01D11/16 , F01D25/24 , F02C3/067 , F02K3/072 , F04D27/009 , F04D29/545 , F05D2220/32 , F05D2240/24 , F05D2240/55 , F05D2260/52
摘要： The present disclosure is directed to a gas turbine engine including a turbine rotor, a turbine frame at least partially surrounding the turbine rotor, and an outer diameter seal assembly. The turbine rotor includes an inner shroud, an outer shroud, and at least one connecting airfoil coupling the inner shroud and the outer shroud. The outer shroud includes a plurality of outer shroud airfoils extended inward along a radial direction. The outer diameter seal assembly includes a sliding portion disposed between the turbine frame and the outer shroud of the turbine rotor. The outer diameter seal assembly defines a secondary tooth at the outer shroud radially inward of a longitudinal face of the sliding portion, and a primary tooth defined axially adjacent to a radial face of the sliding portion.
-
公开(公告)号：US20190017606A1
公开(公告)日：2019-01-17
申请号：US15650457
申请日：2017-07-14
发明人： Conway Chuong , Tara L. D'Ambruoso , Joey Wong
CPC分类号： F16J15/442 , F01D5/03 , F01D11/025 , F01D11/12 , F01D25/22 , F03B3/12 , F03B3/16 , F03D9/34 , F05D2240/53
摘要： A non-contact seal assembly includes a plurality of seal shoes arranged about a centerline in an annular array, the seal shoes including a first seal shoe extending axially along the centerline between a first shoe end and a second shoe end. The non-contact seal assembly may comprise a seal base circumscribing axially offset from the annular array of the seal shoes. The non-contact seal assembly may further comprise a plurality of spring elements, each of the spring elements radially distal from and connecting to a respective one of the seal shoes, and each of the plurality of spring elements is axially adjacent to the seal base.
-
公开(公告)号：US20180363507A1
公开(公告)日：2018-12-20
申请号：US16063050
申请日：2016-12-14
发明人： Clément ROUSSILLE , Thierry TESSON
CPC分类号： F01D25/246 , F01D11/025 , F01D11/18 , F05D2230/642 , F05D2230/644 , F05D2240/11 , F05D2300/6033
摘要： A turbine ring assembly includes ring sectors forming a turbine ring, and a ring support structure having two annular flanges, each ring sector having a portion forming an annular base with an inner face defining the inside face of the turbine ring and an outer face from which there project at least two tabs, the tabs being retained between the two annular flanges. Each tab of the ring sectors includes a projecting portion on its face situated facing one of the two annular flanges, this projecting portion co-operating with a housing present in the annular flange. Each tab of the ring sectors includes an opening in which there is received a portion of a retention element secured to the annular flange situated facing the tab. The retention element is made of a material having a thermal expansion coefficient that is greater than that of the material of the ring sectors.
-
公开(公告)号：US20180328210A1
公开(公告)日：2018-11-15
申请号：US15978671
申请日：2018-05-14
申请人： Dresser-Rand Company
CPC分类号： F01D11/025 , F01D25/12 , F01D25/162 , F01D25/168 , F01D25/26 , F01K25/103 , F05D2220/30
摘要： An expander may include a longitudinal axis, an inner casing split horizontally along the longitudinal axis, an outer casing split horizontally along the longitudinal axis and spaced radially outward from and encompassing the inner casing. Each axial end of the outer casing may form a respective gland seal housing, and the outer casing and inner casing may define an exhaust chamber therebetween. A plurality of expansion stages including a rotor shaft may be disposed within the inner casing and configured to expand the working fluid received from a working fluid source. A plurality of seals may be disposed within each of the gland seal housings and mounted circumferentially about the rotor shaft. The plurality of seals may include an annular seal, a plurality of dynamically self-adjustable seals disposed outboard of the annular seal, and at least one dry gas seal disposed outboard of the plurality of dynamically self-adjustable seals.
-
公开(公告)号：US20180320597A1
公开(公告)日：2018-11-08
申请号：US15772959
申请日：2016-10-12
发明人： Dieter Nass , Gregor Senyk
IPC分类号： F02C7/28
CPC分类号： F02C7/28 , F01D11/025 , F04D29/403 , F05B2230/60 , F05D2220/31 , F05D2230/60 , F05D2240/58
摘要： A method for assembling a turbomachine, the turbomachine has an inner part for arranging in an outer case, which has a parting joint extending along an axis and is divisible into an outer-case upper part and an outer-case lower part. The inner part has rotor parts for rotating about the axis during operation and static components and has at least one seal extending in the circumferential direction for sealing a gap between the inner part and a sealing surface of the outer case. The method includes: providing the outer-case lower part, inserting the inner part into the outer-case lower part in a first axial position, joining the outer-case lower part and outer-case upper part, axially moving the inner part in the outer case in relation to the outer case from the first axial position into an axial end position such that the seal comes in contact with the sealing surface.
-
公开(公告)号：US20180156056A1
公开(公告)日：2018-06-07
申请号：US15368227
申请日：2016-12-02
CPC分类号： F01D11/025 , F01D9/065 , F01D11/24 , F01D17/12 , F01D25/243 , F01D25/26 , F05D2220/32 , F05D2230/22
摘要： An engine or engine casing having an inner annular case and an outer annular case. The engine casing is formed using an additive manufacturing technique such that the inner annular case and outer annular case is formed surrounding a hollow inner annular cavity. The annular cavity includes a pin bank connecting the inner annular case and outer annular case. The pin bank improves heat transfer between the inner and outer annular case and provide structural support to the inner and outer annular case. By providing fluid flow through the annular cavity, the turbine casing can be cooled and the radius of the casing can be controlled through the regulation of fluid travelling within the annular cavity. By controlling the fluid flow though the annular cavity, the engine case may be cooled to regulate its temperature in a wide variety of operating conditions. Further, the regulation of fluid in the annular cavity allows for active clearance control of the spacing between the turbine blades or vanes and seals used in the turbine.
-
-
-
-
-
-
-
-
-
搜索结果
483 条记录 (耗时 0.023 秒)
