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公开(公告)号：US20200149399A1
公开(公告)日：2020-05-14
申请号：US15891401
申请日：2018-02-08
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Nicholas Joseph Kray , Nitesh Jain , Nagashiresha Gontla , Narendra Digamber Joshi , Paul Gerard Marsland , Wayne Allen Spence
Abstract: A blade and a turbomachine engine having the blade are disclosed. The blade includes an airfoil having a root portion, a tip portion, and a plurality of fins integrally coupled to the root portion. The plurality of fins is disposed along a thickness of the airfoil.
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公开(公告)号：US10196898B2
公开(公告)日：2019-02-05
申请号：US14950343
申请日：2015-11-24
Applicant: General Electric Company
Inventor： Nicholas Joseph Kray , Narendra Digamber Joshi , Samar Jyoti Kalita , Paul Gerard Marsland , Wayne Allen Spence
IPC: F01D5/14 , F01D5/28 , F01D9/04 , F01D11/18 , B33Y10/00 , B33Y80/00 , B22F3/105 , B22F7/06 , B22F5/04 , F04D29/02 , F04D29/32 , F04D29/54
Abstract: A turbine engine airfoil apparatus, including an airfoil defined by a plurality of airfoil sections arrayed along a stacking axis that extends between a root and a tip, wherein at least two of the airfoil sections spaced apart from each other have differing airfoil section thermal expansion properties.
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公开(公告)号：US20200024956A1
公开(公告)日：2020-01-23
申请号：US16226703
申请日：2018-12-20
Applicant: General Electric Company
Inventor： Nicholas Joseph Kray , Narendra Digamber Joshi , Samar Jyoti Kalita , Paul Gerard Marsland , Wayne Allen Spence
IPC: F01D5/14 , F01D11/18 , B22F3/105 , B22F5/04 , B22F7/06 , B33Y80/00 , B33Y10/00 , F01D5/28 , F01D9/04
Abstract: A turbine engine airfoil apparatus, including an airfoil defined by a plurality of airfoil sections arrayed along a stacking axis that extends between a root and a tip, wherein at least two of the airfoil sections spaced apart from each other have differing airfoil section thermal expansion properties.
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Patent Agency Ranking
公开(公告)号：US11225871B2
公开(公告)日：2022-01-18
申请号：US16226703
申请日：2018-12-20
Applicant: General Electric Company
Inventor： Nicholas Joseph Kray , Narendra Digamber Joshi , Samar Jyoti Kalita , Paul Gerard Marsland , Wayne Allen Spence
IPC: F01D5/14 , F01D11/18 , B22F5/04 , B22F7/06 , B33Y80/00 , B33Y10/00 , B22F10/20 , F01D5/28 , F01D9/04 , F04D29/32 , F04D29/54
Abstract: A turbine engine airfoil apparatus, including an airfoil defined by a plurality of airfoil sections arrayed along a stacking axis that extends between a root and a tip, wherein at least two of the airfoil sections spaced apart from each other have differing airfoil section thermal expansion properties.
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公开(公告)号：US10830067B2
公开(公告)日：2020-11-10
申请号：US15923545
申请日：2018-03-16
Applicant: General Electric Company
Inventor： Nicholas Joseph Kray , Paul Gerard Marsland , Wayne Allen Spence , Abhijeet Yadav , Samar Jyoti Kalita , Nitesh Jain , Narendra D. Joshi
Abstract: An airfoil for a turbomachinery rotor includes: a body having a first density, the body defining a pressure side and a suction side, the pressure side and suction side intersecting at a leading edge and a trailing edge; and a mass positioned within the body and having a second density, wherein the second density is greater than the first density, wherein the mass is offset from a center of gravity of the body in at least one axis.
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公开(公告)号：US10724376B2
公开(公告)日：2020-07-28
申请号：US15891401
申请日：2018-02-08
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Nicholas Joseph Kray , Nitesh Jain , Nagashiresha Gontla , Narendra Digamber Joshi , Paul Gerard Marsland , Wayne Allen Spence
Abstract: A blade and a turbomachine engine having the blade are disclosed. The blade includes an airfoil having a root portion, a tip portion, and a plurality of fins integrally coupled to the root portion. The plurality of fins is disposed along a thickness of the airfoil.
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公开(公告)号：US20190284943A1
公开(公告)日：2019-09-19
申请号：US15923545
申请日：2018-03-16
Applicant: General Electric Company
Inventor： Nicholas Joseph Kray , Paul Gerard Marsland , Wayne Allen Spence , Abhijeet Yadav , Samar Jyoti Kalita , Nitesh Jain , Narendra D. Joshi
Abstract: An airfoil for a turbomachinery rotor includes: a body having a first density, the body defining a pressure side and a suction side, the pressure side and suction side intersecting at a leading edge and a trailing edge; and a mass positioned within the body and having a second density, wherein the second density is greater than the first density, wherein the mass is offset from a center of gravity of the body in at least one axis.
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公开(公告)号：US20170146021A1
公开(公告)日：2017-05-25
申请号：US14950343
申请日：2015-11-24
Applicant: General Electric Company
Inventor： Nicholas Joseph Kray , Narendra Digamber Joshi , Samar Jyoti Kalita , Paul Gerard Marsland , Wayne Allen Spence
CPC classification number: F01D5/147 , B22F3/1055 , B22F5/04 , B22F7/06 , B22F2207/01 , B33Y10/00 , B33Y80/00 , F01D5/148 , F01D5/28 , F01D9/041 , F01D11/18 , F04D29/023 , F04D29/321 , F04D29/541 , F05D2220/32 , F05D2230/22 , F05D2230/31 , F05D2300/50212 , Y02P10/295
Abstract: A turbine engine airfoil apparatus, including an airfoil defined by a plurality of airfoil sections arrayed along a stacking axis that extends between a root and a tip, wherein at least two of the airfoil sections spaced apart from each other have differing airfoil section thermal expansion properties.
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