-
公开(公告)号：US09777744B2
公开(公告)日：2017-10-03
申请号：US14845358
申请日：2015-09-04
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Paul Griffin Deivernois , Jeremy Peter Latimer
CPC classification number: F04D29/324 , F01D5/141 , F01D9/041 , F05D2250/74
Abstract: An article of manufacture having a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in a scalable TABLE 1, wherein the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y, and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete airfoil shape.
-
12.发明申请公开(公告)号：US20140271109A1
公开(公告)日：2014-09-18
申请号：US13834745
申请日：2013-03-15
Applicant: General Electric Company
Inventor： Jeremy Peter Latimer , Eric Richard Bonini , John Duong
IPC: F01D11/00
CPC classification number: F01D5/3007 , F01D5/085
Abstract: The present application and the resultant patent provide an axial compressor for a gas turbine engine. The compressor may include a rotor disk positioned along an axis of the compressor. The rotor disk may include a slot defined about a radially outer surface of the rotor disk, and the slot may include a slot planar surface facing away from the rotor disk. The compressor also may include a compressor blade coupled to the rotor disk via the slot. The compressor blade may include a platform positioned over the radially outer surface of the rotor disk, and the platform may include a platform sealing edge facing toward the rotor disk. The compressor further may include a gap defined between the platform sealing edge and the slot planar surface, wherein the gap is configured to control a flow of leakage air from a high-pressure side of the compressor blade to a low-pressure side of the compressor blade. The present application and the resultant patent further provide a related method of controlling stage-to-stage leakage in an axial compressor of a gas turbine engine.
Abstract translation: 本申请和所得专利提供了一种用于燃气涡轮发动机的轴向压缩机。 压缩机可以包括沿着压缩机的轴线定位的转子盘。 转子盘可以包括围绕转子盘的径向外表面限定的槽，并且槽可以包括面向转子盘的槽平面。 压缩机还可以包括经由槽连接到转子盘的压缩机叶片。 压缩机叶片可以包括定位在转子盘的径向外表面上方的平台，并且平台可以包括面向转子盘的平台密封边缘。 压缩机还可以包括限定在平台密封边缘和槽平面之间的间隙，其中间隙构造成控制从压缩机叶片的高压侧到压缩机的低压侧的泄漏空气流 刀。 本申请和所得专利进一步提供了一种在燃气轮机的轴向压缩机中控制级间泄漏的相关方法。
-
公开(公告)号：US12018585B2
公开(公告)日：2024-06-25
申请号：US18192162
申请日：2023-03-29
Applicant: General Electric Company
Inventor： Marc Edward Blohm , Vasantharuban S , Michael James Dutka , Nandakumar A R , Sharan Shanti , Prakash Dalsania , Corey Lynn Hubbert , Siddaraja Mallikarjuna Devangada , Joshy John , Nancy Chaudhary , Abel Christena Francis , Brandon Lamar Bush , Jeremy Peter Latimer
CPC classification number: F01D5/141 , F05D2220/3217 , F05D2220/3219 , F05D2240/301 , F05D2240/306 , F05D2250/74
Abstract: A rotor blade includes an airfoil having an airfoil shape. The airfoil shape has a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in one of Table I, Table II, Table III, Table IV, Table V, Table VI, Table VII, Table VIII, or Table IX. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances expressed in a unit of distance by multiplying the Cartesian coordinate values of X, Y and Z by a scaling factor of the airfoil in the unit of distance. The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each Z value. The airfoil profile sections at Z values are joined smoothly with one another to form a complete airfoil shape.
-
Patent Agency Ranking
公开(公告)号：US11480062B1
公开(公告)日：2022-10-25
申请号：US17445210
申请日：2021-08-17
Applicant: General Electric Company
Inventor： Paul G. Deivernois , Vasantharuban S , Michael James Dutka , Narasimha K V Rao , Timothy E. DeJoris , Nancy Chaudhary , Marc Edward Blohm , Sunil Rajagopal , Prakash Dalsania , Steven Lynn Huskins , Siddaraja Mallikarjuna Devangada , Bala Muralidhar Singh B , Aaron David Williamson , Joshy John , Nandakumar A R , Jeremy Peter Latimer , Phillip Matthew Malloy
IPC: F01D9/04
Abstract: A stator vane includes an airfoil having an airfoil shape. The airfoil shape has a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in one of Table I, Table II, Table III, Table IV, Table V, Table VI, Table VII, or Table VIII. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances expressed in a unit of distance by multiplying the Cartesian coordinate values of X, Y and Z by a scaling factor of the airfoil in the unit of distance. The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each Z value. The airfoil profile sections at Z values are joined smoothly with one another to form a complete airfoil shape.
-
公开(公告)号：US11293454B1
公开(公告)日：2022-04-05
申请号：US17244989
申请日：2021-04-30
Applicant: General Electric Company
Inventor： Paul G. Deivernois , Marcus Edward Blohm , Michael James Dutka , Andrew Clifford Hart , Steven Lynn Huskins , Aaron David Williamson , Corey Lynn Hubbert , Venkata Siva Prasad Chaluvadi , Brandon Lamar Bush , Jeremy Peter Latimer
Abstract: A stator vane includes an airfoil having an airfoil shape. The airfoil shape having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in one of Table I, Table II, Table III, Table IV, Table V, Table VI, Table VII, or Table VIII. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances expressed in a unit of distance by multiplying the Cartesian coordinate values of X, Y and Z by a scaling factor of the airfoil in the unit of distance. The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each Z value. The airfoil profile sections at Z values being joined smoothly with one another to form a complete airfoil shape.
-
公开(公告)号：US20170067476A1
公开(公告)日：2017-03-09
申请号：US14845358
申请日：2015-09-04
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Paul Griffin Deivernois , Jeremy Peter Latimer
IPC: F04D29/32
CPC classification number: F04D29/324 , F01D5/141 , F01D9/041 , F05D2250/74
Abstract: An article of manufacture having a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in a scalable TABLE 1, wherein the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y, and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete airfoil shape.
-
17.发明授权公开(公告)号：US09470098B2
公开(公告)日：2016-10-18
申请号：US13834745
申请日：2013-03-15
Applicant: General Electric Company
Inventor： Jeremy Peter Latimer , Eric Richard Bonini , John Duong
CPC classification number: F01D5/3007 , F01D5/085
Abstract: The present application and the resultant patent provide an axial compressor for a gas turbine engine. The compressor may include a rotor disk positioned along an axis of the compressor. The rotor disk may include a slot defined about a radially outer surface of the rotor disk, and the slot may include a slot planar surface facing away from the rotor disk. The compressor also may include a compressor blade coupled to the rotor disk via the slot. The compressor blade may include a platform positioned over the radially outer surface of the rotor disk, and the platform may include a platform sealing edge facing toward the rotor disk. The compressor further may include a gap defined between the platform sealing edge and the slot planar surface, wherein the gap is configured to control a flow of leakage air from a high-pressure side of the compressor blade to a low-pressure side of the compressor blade. The present application and the resultant patent further provide a related method of controlling stage-to-stage leakage in an axial compressor of a gas turbine engine.
Abstract translation: 本申请和所得专利提供了一种用于燃气涡轮发动机的轴向压缩机。 压缩机可以包括沿着压缩机的轴线定位的转子盘。 转子盘可以包括围绕转子盘的径向外表面限定的槽，并且槽可以包括面向转子盘的槽平面。 压缩机还可以包括经由槽连接到转子盘的压缩机叶片。 压缩机叶片可以包括定位在转子盘的径向外表面上方的平台，并且平台可以包括面向转子盘的平台密封边缘。 压缩机还可以包括限定在平台密封边缘和槽平面之间的间隙，其中间隙构造成控制从压缩机叶片的高压侧到压缩机的低压侧的泄漏空气流 刀。 本申请和所得专利进一步提供了一种在燃气轮机的轴向压缩机中控制级间泄漏的相关方法。
-
公开(公告)号：US20160186592A1
公开(公告)日：2016-06-30
申请号：US14587736
申请日：2014-12-31
Applicant: General Electric Company
Inventor： Michael James Healy , Jeremy Peter Latimer
CPC classification number: F01D5/3007 , F01D11/08 , F05D2240/11 , Y02T50/671 , Y02T50/673
Abstract: A gas turbine that having a flowpath having a rotor assembly that includes: a first rotor wheel supporting a first rotor blade having a platform that defines a first axial section of an inner boundary of the flowpath; a second rotor wheel supporting a second rotor blade having a platform that defines a second axial section of the inner boundary of the flowpath; and an annulus filler that includes an outboard surface that defines at least part of a third axial section of the inner boundary of the flowpath occurring between the first axial section and the second axial section of the inner boundary of the flowpath. The first rotor wheel may include an axial connector for axially engaging a mating surface formed on a radially innermost face of the first rotor blade and a mating surface formed on a radially innermost face of the annulus filler.
-
-
-
-
-
-
-
Search Results
18
records
(took 0.02 seconds)
