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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
Applicant: General Electric Company
Inventor： Steven Douglas Johnson , Julius John Montgomery , Brandon Wayne Miller , Robert Proctor , Bradley W. Fintel , Jeffrey Douglas Rambo
Abstract: 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：US11221140B2
公开(公告)日：2022-01-11
申请号：US16907013
申请日：2020-06-19
Applicant: General Electric Company
Inventor： Jinjie Shi , Stephen Gerard Schadewald , Jason Paul Hoppa , Kirk Douglas Gallier , Christopher Edward Wolfe , Robert Proctor
Abstract: A seal assembly to seal a gas turbine hot gas path flow at an interface of a combustor liner and a downstream component, such as a stage one turbine nozzle, in a gas turbine. The seal assembly including a piston ring seal housing, defining a cavity, and a piston ring disposed within the cavity. The piston ring disposed circumferentially about the combustor liner. The piston ring is responsive to a regulated pressure to secure sealing engagement of the piston ring and outer surface of the combustor liner. The seal assembly includes at least one of one or more sectional through-slots, bumps or channel features to provide for a flow therethrough of a high-pressure (Phigh) bypass airflow exiting a compressor to the cavity. The high-pressure (Phigh) bypass airflow exerting a radial force on the piston ring.
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23.发明授权Device and method for preventing leakage of air between multiple turbine components 有权用于防止多个涡轮机部件之间的空气泄漏的装置和方法公开(公告)号：US09488110B2
公开(公告)日：2016-11-08
申请号：US13790965
申请日：2013-03-08
Applicant: General Electric Company
Inventor： George Joe-Kueng Chan , Victor Hugo Silva Correia , David Hannwacker , Robert Proctor
CPC classification number: F02C7/28 , F01D9/023 , F01D11/005 , F01D25/145 , F05D2230/642 , F05D2250/75 , F05D2260/941 , F05D2300/50211 , F05D2300/6033 , F16J15/0887 , F16J15/52 , F23R3/007 , F23R3/60 , F23R2900/00001 , F23R2900/00012 , F23R2900/00017 , Y02T50/672 , Y02T50/675 , Y10T403/217
Abstract: A turbine comprising a first turbine component being of a first material having a first coefficient of thermal expansion. A second turbine component being of a second material having a second coefficient of thermal expansion, said second turbine component adjacent said first turbine component. A space between said first and second turbine components. A seal assembly sealing said space, wherein at least a portion of said seal assembly has a coefficient of thermal expansion substantially similar to at least one of said first or second turbine components to thereby maintain a seal in said space during thermal expansion or contraction of said first and second turbine components.
Abstract translation: 一种涡轮机，包括具有第一热膨胀系数的第一材料的第一涡轮机部件。 第二涡轮机部件是具有第二热膨胀系数的第二材料，所述第二涡轮部件与所述第一涡轮部件相邻。 所述第一和第二涡轮机部件之间的空间。 一种密封所述空间的密封组件，其中所述密封组件的至少一部分的热膨胀系数基本上类似于所述第一或第二涡轮机部件中的至少一个，从而在所述第一或第二涡轮机部件的热膨胀或收缩期间保持所述空间中的密封 第一和第二涡轮机部件。
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24.发明申请DEVICE AND METHOD FOR PREVENTING LEAKAGE OF AIR BETWEEN MULTIPLE TURBINE COMPONENTS 有权用于防止多个涡轮机组件之间的空气泄漏的装置和方法公开(公告)号：US20140250893A1
公开(公告)日：2014-09-11
申请号：US13790965
申请日：2013-03-08
Applicant: GENERAL ELECTRIC COMPANY
Inventor： George Joe-Kueng Chan , Victor Hugo Silva Correia , David Hannwacker , Robert Proctor
IPC: F02C7/28
CPC classification number: F02C7/28 , F01D9/023 , F01D11/005 , F01D25/145 , F05D2230/642 , F05D2250/75 , F05D2260/941 , F05D2300/50211 , F05D2300/6033 , F16J15/0887 , F16J15/52 , F23R3/007 , F23R3/60 , F23R2900/00001 , F23R2900/00012 , F23R2900/00017 , Y02T50/672 , Y02T50/675 , Y10T403/217
Abstract: A turbine comprising a first turbine component being of a first material having a first coefficient of thermal expansion. A second turbine component being of a second material having a second coefficient of thermal expansion, said second turbine component adjacent said first turbine component. A space between said first and second turbine components. A seal assembly sealing said space, wherein at least a portion of said seal assembly has a coefficient of thermal expansion substantially similar to at least one of said first or second turbine components to thereby maintain a seal in said space during thermal expansion or contraction of said first and second turbine components.
Abstract translation: 一种涡轮机，包括具有第一热膨胀系数的第一材料的第一涡轮机部件。 第二涡轮机部件是具有第二热膨胀系数的第二材料，所述第二涡轮部件与所述第一涡轮部件相邻。 所述第一和第二涡轮机部件之间的空间。 一种密封所述空间的密封组件，其中所述密封组件的至少一部分具有与所述第一或第二涡轮机部件中的至少一个基本相似的热膨胀系数，从而在所述第一或第二涡轮部件的热膨胀或收缩期间保持所述空间中的密封 第一和第二涡轮机部件。
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公开(公告)号：US20140030066A1
公开(公告)日：2014-01-30
申请号：US13743818
申请日：2013-01-17
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Scott Alan Schimmels , Daniel John Fusinato , John Carl Glessner , Dan Nicholas Mirkovich , Robert Proctor
IPC: F01D11/24
CPC classification number: F01D11/24 , F01D25/12 , F01D25/14 , F05D2200/33 , F05D2260/201 , F05D2260/30 , Y02T50/676
Abstract: Active clearance control systems for gas turbine engines are disclosed. An example active clearance control system may include a generally circumferentially mounted spray tube comprising a plurality of impingement holes arranged to impinge thermal control air on a clearance control component of a case; a rigid mounting assembly substantially rigidly coupling the spray tube to the case; and/or a sliding mounting assembly coupling the spray tube to the case while permitting limited relative movement between the spray tube and the case in a direction generally parallel with an engine axis. The sliding mount may be coupled to the case generally axially forward of the rigid mount. A ratio of the stand-off distance to the impingement hole diameter may be less than about 8. A ratio of the arc spacing to the impingement hole diameter may be less than about 15.
Abstract translation: 公开了用于燃气涡轮发动机的主动间隙控制系统。 示例性主动间隙控制系统可以包括大致周向安装的喷射管，其包括多个冲击孔，其被布置成将热控制空气撞击到壳体的间隙控制部件上; 将喷射管基本上刚性地连接到壳体上的刚性安装组件; 和/或滑动安装组件，其将喷射管连接到壳体，同时允许喷射管和壳体在大致平行于发动机轴线的方向上的有限的相对运动。 滑动安装件可以连接到刚性安装座的大致轴向前方的壳体。 间隔距离与冲击孔直径的比值可以小于约8.弧距与冲击孔直径的比可以小于约15。
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Patent Agency Ranking
公开(公告)号：US11976562B2
公开(公告)日：2024-05-07
申请号：US18297835
申请日：2023-04-10
Applicant: General Electric Company
Inventor： Steven Douglas Johnson , Julius John Montgomery , Brandon Wayne Miller , Robert Proctor , Bradley W. Fintel , Jeffrey Douglas Rambo
CPC classification number: F01D11/24 , F01D5/03 , F01D11/18 , F02C6/08 , F02C7/185 , F01D25/12 , F01D25/14 , F05D2220/323 , F05D2240/11 , F05D2240/55 , F05D2260/20 , F05D2260/30
Abstract: 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：US20220128236A1
公开(公告)日：2022-04-28
申请号：US17647235
申请日：2022-01-06
Applicant: General Electric Company
Inventor： Jinjie Shi , Robert Proctor , Jason Paul Hoppa , Stephen Gerard Schadewald , Christopher Edward Wolfe , Kirk Douglas Gallier
Abstract: A seal assembly to seal a gas turbine hot gas path flow at an interface of a combustor liner and a downstream component, such as a stage one turbine nozzle, in a gas turbine. The seal assembly including a piston ring seal housing, defining a cavity, and a piston ring disposed within the cavity. The piston ring disposed circumferentially about the combustor liner. The piston ring is responsive to a regulated pressure to secure sealing engagement of the piston ring and outer surface of the combustor liner. The seal assembly includes at least one of one or more sectional through-slots, bumps or channel features to provide for a flow therethrough of a high-pressure (Phigh) bypass airflow exiting a compressor to the cavity. The high-pressure (Phigh) bypass airflow exerting a radial force on the piston ring.
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公开(公告)号：US20210031937A1
公开(公告)日：2021-02-04
申请号：US16941730
申请日：2020-07-29
Applicant: General Electric Company
Inventor： Scott Alan Schimmels , Jeffrey Douglas Rambo , Thomas Kupiszewski , Paul Alexander Intemann , Robert Proctor
Abstract: A vehicle is provided including a structure including a skin defining an outside surface exposed to ambient cooling flow and an inside surface. The structure includes a first structural member extending from the inside surface of the skin and a second structural member extending from the inside surface of the skin; and a thermal management system including a heat exchanger assembly positioned adjacent to, and in thermal communication with, the inside surface of the skin, the heat exchanger assembly positioned at least partially between the first and second structural members of the structure.
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公开(公告)号：US20200318831A1
公开(公告)日：2020-10-08
申请号：US16907013
申请日：2020-06-19
Applicant: General Electric Company
Inventor： Jinjie Shi , Stephen Gerard Schadewald , Jason Paul Hoppa , Kirk Douglas Gallier , Christopher Edward Wolfe , Robert Proctor
Abstract: A seal assembly to seal a gas turbine hot gas path flow at an interface of a combustor liner and a downstream component, such as a stage one turbine nozzle, in a gas turbine. The seal assembly including a piston ring seal housing, defining a cavity, and a piston ring disposed within the cavity. The piston ring disposed circumferentially about the combustor liner. The piston ring is responsive to a regulated pressure to secure sealing engagement of the piston ring and outer surface of the combustor liner. The seal assembly includes at least one of one or more sectional through-slots, bumps or channel features to provide for a flow therethrough of a high-pressure (Phigh) bypass airflow exiting a compressor to the cavity. The high-pressure (Phigh) bypass airflow exerting a radial force on the piston ring.
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公开(公告)号：US20200011347A1
公开(公告)日：2020-01-09
申请号：US16555558
申请日：2019-08-29
Applicant: General Electric Company
Inventor： Sesha Subramanian , Monty Lee Shelton , Robert Proctor , Mohamed Musthafa Thoppil , Venkateswararao Gurram , Josiah Warren Joiner , Wojciech Sak
Abstract: An apparatus and method of cooling a hot portion of a gas turbine engine, such as a multi-stage compressor of a gas turbine engine, by reducing an operating air temperature in a space between a seal and a blade post of adjacent stages by routing cooling air through an inlet in the vane, passing the routed cooling air through the vane, and emitting the routed cooling air into the space.
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