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Patent Agency Ranking
公开(公告)号：US11795877B2
公开(公告)日：2023-10-24
申请号：US17906756
申请日：2020-03-24
Applicant: Siemens Energy, Inc.
Inventor： Ashok Reddy Gitta , Damien G. Teehan , Yan Yin , Chirag Patel , John T. Fetherolf, Jr.
CPC classification number: F02C7/18 , F02C9/18 , F01D25/12 , F05D2220/32 , F05D2230/80 , F05D2260/20
Abstract: A method of modulating a cooling supply in a gas turbine engine includes providing the engine comprising a compressor section and a turbine section and including a cooling flow circuit, the cooling flow circuit supplying a cooling air flow from a compressor cavity in the compressor section to a blade ring cavity in the turbine section, wherein the cooling flow circuit includes a main line with a full capacity valve, measuring a first pressure in the blade ring cavity, measuring a second pressure in the compressor cavity, adjusting, by a control system, the opening of the full capacity valve to control the cooling air flow through the main line in order to maintain a target pressure ratio, wherein the pressure ratio defined as a ratio of the first pressure to the second pressure. The method is performed in an ambient temperature operating range of the engine.
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公开(公告)号：US20180223683A1
公开(公告)日：2018-08-09
申请号：US15743117
申请日：2015-07-20
Applicant: Siemens Energy, Inc.
Inventor： Kok-Mun Tham , Abdullatif M. Chehab , Patrick M. Pilapil , Yan Yin , Christian Xavier Campbell , Vincent Paul Laurello
CPC classification number: F01D11/001 , F01D5/081 , F01D11/02 , F01D25/12
Abstract: A turbine arrangement including a rotor and a stator surrounding the rotor and comprising guide vane segments, each guide vane segment comprising an airfoil and a radially inner vane platform. A seal arrangement includes a static seal inward from the inner vane platforms and having a radially extending face plate, first and second cylindrical seal walls extending from outer and inner ends of the annular face plate, an annular seal plate extending radially from the second cylindrical seal wall, and an angel wing extending between the first cylindrical seal wall and the annular seal plate to define a first annular cavity and a second annular cavity. Circumferentially spaced cut-outs define passages through the annular seal plate between the first and second annular cavities and are aligned with fasteners that attach the annular face plate to a support ring for supporting the inner vane platform.
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公开(公告)号：US10215044B2
公开(公告)日：2019-02-26
申请号：US15325527
申请日：2014-08-08
Applicant: Siemens Energy, Inc.
Inventor： Jiping Zhang , Patrick M. Pilapil , Yan Yin , Joshua D. Kovac
Abstract: An interstage seal system (10) for adjusting the position of an interstage seal during operation of a gas turbine engine (14) to increase efficiency of the seal (12) is disclosed. The interstage seal system (10) may include a interstage seal housing (16) formed from a circumferentially extending housing having a seal (12) positioned on a radially inward surface (18) of the interstage seal housing (16). The interstage seal housing (16) may biased radially outward via one or more springs (20) to bias the radially inward surface (18) of the interstage seal housing (16) outwardly. The interstage seal housing (16) may reside in an interstage housing receiving cavity (68). The cavity (68) may be supplied with gases at a higher pressure than on the other side (24) of the seal housing (16) during turbine engine operation. As such, the interstage seal housing (16) is forced radially inwardly to close the gap (26) within the seal (12) as the high pressure force directed radially inward overcomes the spring bias directed radially outward.
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公开(公告)号：US20230122896A1
公开(公告)日：2023-04-20
申请号：US17906756
申请日：2020-03-24
Applicant: Siemens Energy, Inc.
Inventor： Ashok Reddy Gitta , Damien G. Teehan , Yan Yin , Chirag Patel , John T. Fetherolf, Jr.
Abstract: A method of modulating a cooling supply in a gas turbine engine includes providing the engine comprising a compressor section and a turbine section and including a cooling flow circuit, the cooling flow circuit supplying a cooling air flow from a compressor cavity in the compressor section to a blade ring cavity in the turbine section, wherein the cooling flow circuit includes a main line with a full capacity valve, measuring a first pressure in the blade ring cavity, measuring a second pressure in the compressor cavity, adjusting, by a control system, the opening of the full capacity valve to control the cooling air flow through the main line in order to maintain a target pressure ratio, wherein the pressure ratio defined as a ratio of the first pressure to the second pressure. The method is performed in an ambient temperature operating range of the engine.
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公开(公告)号：US20170145847A1
公开(公告)日：2017-05-25
申请号：US15325527
申请日：2014-08-08
Applicant: Siemens Energy, Inc.
Inventor： Jiping Zhang , Patrick M. Pilapil , Yan Yin , Joshua D. Kovac
CPC classification number: F01D11/003 , F01D11/02 , F01D11/025 , F01D25/26 , F05D2220/32 , F05D2240/70 , F05D2260/52 , F16J15/445
Abstract: An interstage seal system (10) for adjusting the position of an interstage seal during operation of a gas turbine engine (14) to increase efficiency of the seal (12) is disclosed. The interstage seal system (10) may include a interstage seal housing (16) formed from a circumferentially extending housing having a seal (12) positioned on a radially inward surface (18) of the interstage seal housing (16). The interstage seal housing (16) may biased radially outward via one or more springs (20) to bias the radially inward surface (18) of the interstage seal housing (16) outwardly. The interstage seal housing (16) may reside in an interstage housing receiving cavity (68). The cavity (68) may be supplied with gases at a higher pressure than on the other side (24) of the seal housing (16) during turbine engine operation. As such, the interstage seal housing (16) is forced radially inwardly to close the gap (26) within the seal (12) as the high pressure force directed radially inward overcomes the spring bias directed radially outward.
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