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公开(公告)号：US11668207B2
公开(公告)日：2023-06-06
申请号：US15316577
申请日：2015-04-23
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Jason David Shapiro , Jan Christopher Schilling , Michael John Franks
CPC classification number: F01D25/246 , F01D25/12 , F01D25/24 , F05D2220/32 , F05D2250/131 , F05D2300/50212 , Y02T50/60
Abstract: A shroud hanger assembly or shroud assembly is provided for dimensionally incompatible components wherein the assembly includes a multi-piece hanger, for example having a forward hanger portion and a rearward hanger portion. A cavity is formed between the parts; wherein a shroud may be positioned which is formed of a low coefficient of thermal expansion material. The hanger and shroud may be formed of the same material or differing materials in order to better match the thermal growth between the hanger and the shroud. When the shroud is positioned within the hanger opening or cavity, one of the forward and rearward hanger portions may be press fit or otherwise connected into the other of the forward and rearward hanger portion.
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公开(公告)号：US11215081B2
公开(公告)日：2022-01-04
申请号：US16462355
申请日：2015-05-06
Applicant: General Electric Company
Inventor： Jan Christopher Schilling , Andrew John Breslin , Bryce Loring Heitman
Abstract: A shroud hanger assembly is provided for hangers and shrouds defining dimensionally incompatible components such as those which are press or frictionally fit to engage one another. The shroud hanger assembly includes a multi-piece hanger and a shroud, which is pinned to the hanger assembly by at least one axially extending pin and which locates the shroud relative to the hanger to control motion in one or both of circumferential (tangential) and radial directions relative to the engine.
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公开(公告)号：US12196099B2
公开(公告)日：2025-01-14
申请号：US18398597
申请日：2023-12-28
Applicant: General Electric Company
Inventor： Jan Christopher Schilling , Andrew John Breslin , Bryce Loring Heitman
Abstract: A shroud hanger assembly is provided for hangers and shrouds defining dimensionally incompatible components such as those which are press or frictionally fit to engage one another. The shroud hanger assembly includes a multi-piece hanger and a shroud that is pinned to the hanger assembly by at least one axially extending pin and which locates the shroud relative to the hanger to control motion in one or both of circumferential (tangential) and radial directions relative to the engine.
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公开(公告)号：US10138752B2
公开(公告)日：2018-11-27
申请号：US15053276
申请日：2016-02-25
Applicant: General Electric Company
Inventor： Jan Christopher Schilling
Abstract: A gas turbine engine clearance control system includes a cooling air passage extending from a cooling air inlet port to a cooling air outlet port. The cooling air inlet port and outlet port are formed within an external surface of a compressor casing of a compressor and are also axially spaced on the external surface of the compressor casing. The cooling air passage extends from the cooling air inlet port radially inwardly to at least one of a flange joint, a radially outer surface of a compressor casing ring, and a radially outer surface of a connector case. The cooling air passage further extends aftward along the radially outer surfaces of the connector case and the compressor casing ring. The cooling air passage further extends radially outward to the cooling air outlet port. Selectively supplying cooling air to the cooling air passage controls a rotor tip clearance between a rotor tip of a rotor blade of the compressor and an inner surface of the compressor casing ring and further controls an interstage seal clearance between an inner band and a rotor spool of the compressor.
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公开(公告)号：US10145382B2
公开(公告)日：2018-12-04
申请号：US14985169
申请日：2015-12-30
Applicant: General Electric Company
Inventor： Nicholas Joseph Kray , Jan Christopher Schilling , Nitesh Jain , Abhijit Roy
Abstract: A composite blade assembly and a method of assembling a composite blade are provided. The composite blade assembly includes a composite blade having a radially inner root. A composite blade assembly includes a first platform and a circumferentially adjacent second platform abutting the first platform at a platform joint. Each of the first platform and the second platform includes a radially outer surface and a radially inwardly extending attachment member. The platform joint includes a slot extending through adjacent edges of the first platform and the second platform. The slot is configured to receive the radially inner root and the radially inner root is configured to be sandwiched between the attachment members. The blade assembly includes an adhesive system configured to join the radially inner root of the composite blade and the attachment members into a unitary structure, and a retaining clip configured to bias the attachment members towards each other.
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Patent Agency Ranking
公开(公告)号：US09309772B2
公开(公告)日：2016-04-12
申请号：US13774581
申请日：2013-02-22
Applicant: General Electric Company
Inventor： Ross Ashely Spoonire , Wendy Wen-Ling Lin , Jan Christopher Schilling , Dong Jin Shim , Gregory Carl Gemeinhardt , Prakash Kashiram Jadhav
CPC classification number: F01D5/282 , F01D5/288 , F04D29/023 , F04D29/324 , F05D2220/36 , F05D2300/43 , F05D2300/603 , Y02T50/672 , Y02T50/673 , Y10T156/10 , Y10T156/1002
Abstract: A hybrid turbine blade and method of fabrication, comprising a shank portion and an airfoil portion. The airfoil portion comprising a composite outer structure having a recess formed therein and an alternating stack of at least one composite section and at least two insert sections disposed in the recess. The outer composite structure and the at least one composite section having a first density. The at least two insert sections having a second mass density, which is less than the first mass density. The composite outer structure and the alternating stack of at least one composite section and at least two insert sections together define an airfoil portion that meets all mechanical load carrying requirements of said hybrid turbine blade such that no load transfer needs to occur through said at least two insert sections.
Abstract translation: 一种混合涡轮叶片及其制造方法，包括柄部和翼型部。 机翼部分包括具有形成在其中的凹部的复合外部结构和至少一个复合部分的交替堆叠和设置在凹部中的至少两个插入部分。 外部复合结构和至少一个复合部分具有第一密度。 所述至少两个插入部分具有小于第一质量密度的第二质量密度。 至少一个复合部分和至少两个插入部分的复合外部结构和交替堆叠共同限定了一个翼型部分，其满足所述混合式涡轮机叶片的所有机械承载要求，使得不需要通过所述至少两个 插入部分。
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公开(公告)号：US20140294594A1
公开(公告)日：2014-10-02
申请号：US13774581
申请日：2013-02-22
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Ross Ashely Spoonire , Wendy Wen-Ling Lin , Jan Christopher Schilling , Dong Jin Shim , Gregory Carl Gemeinhardt , Prakash Kashiram Jadhav
IPC: F01D5/28
CPC classification number: F01D5/282 , F01D5/288 , F04D29/023 , F04D29/324 , F05D2220/36 , F05D2300/43 , F05D2300/603 , Y02T50/672 , Y02T50/673 , Y10T156/10 , Y10T156/1002
Abstract: A hybrid turbine blade and method of fabrication, comprising a shank portion and an airfoil portion. The airfoil portion comprising a composite outer structure having a recess formed therein and an alternating stack of at least one composite section and at least two insert sections disposed in the recess. The outer composite structure and the at least one composite section having a first density. The at least two insert sections having a second mass density, which is less than the first mass density. The composite outer structure and the alternating stack of at least one composite section and at least two insert sections together define an airfoil portion that meets all mechanical load carrying requirements of said hybrid turbine blade such that no load transfer needs to occur through said at least two insert sections.
Abstract translation: 一种混合涡轮叶片及其制造方法，包括柄部和翼型部。 机翼部分包括具有形成在其中的凹部的复合外部结构和至少一个复合部分的交替堆叠和设置在凹部中的至少两个插入部分。 外部复合结构和至少一个复合部分具有第一密度。 所述至少两个插入部分具有小于第一质量密度的第二质量密度。 至少一个复合部分和至少两个插入部分的复合外部结构和交替堆叠共同限定了一个翼型部分，其满足所述混合式涡轮机叶片的所有机械承载要求，使得不需要通过所述至少两个 插入部分。
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公开(公告)号：US20250101885A1
公开(公告)日：2025-03-27
申请号：US18971470
申请日：2024-12-06
Applicant: General Electric Company
Inventor： Jan Christopher Schilling , Andrew John Breslin , Bryce Loring Heitman
Abstract: A shroud hanger assembly is provided for hangers and shrouds defining dimensionally incompatible components such as those which are press or frictionally fit to engage one another. The shroud hanger assembly includes a multi-piece hanger and a shroud that is pinned to the hanger assembly by at least one axially extending pin and which locates the shroud relative to the hanger to control motion in one or both of circumferential (tangential) and radial directions relative to the engine.
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公开(公告)号：US20230265769A1
公开(公告)日：2023-08-24
申请号：US18308806
申请日：2023-04-28
Applicant: General Electric Company
Inventor： Jason David Shapiro , Jan Christopher Schilling , Michael John Franks
CPC classification number: F01D25/246 , F01D25/24 , F01D25/12 , Y02T50/60 , F05D2220/32 , F05D2250/131 , F05D2300/50212
Abstract: A shroud hanger assembly (30) or shroud assembly is provided for dimensionally incompatible components wherein the assembly includes a multi-piece hanger (32), for example having a forward hanger portion (34) and a rearward hanger portion (36). A cavity (46) is formed between the parts; wherein a shroud (50) may be positioned which is formed of a low coefficient of thermal expansion material. The hanger (32) and shroud (50) may be formed of the same material or differing materials in order to better match the thermal growth between the hanger and the shroud. When the shroud (50) is positioned within the hanger opening or cavity (46), one of the forward (34) and rearward hanger (36) portions may be press fit or otherwise connected into the other of the forward (34) and rearward (36) hanger portion.
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公开(公告)号：US20220120198A1
公开(公告)日：2022-04-21
申请号：US17565528
申请日：2021-12-30
Applicant: General Electric Company
Inventor： Jan Christopher Schilling , Andrew John Breslin , Bryce Loring Heitman
IPC: F01D25/24
Abstract: A shroud hanger assembly is provided for hangers and shrouds defining dimensionally incompatible components such as those which are press or frictionally fit to engage one another. The shroud hanger assembly includes a multi-piece hanger and a shroud that is pinned to the hanger assembly by at least one axially extending pin and which locates the shroud relative to the hanger to control motion in one or both of circumferential (tangential) and radial directions relative to the engine.
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