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公开(公告)号：US10343392B2
公开(公告)日：2019-07-09
申请号：US14837059
申请日：2015-08-27
Applicant: GENERAL ELECTRIC COMPANY
Inventor： William Thomas Carter , Mark Kevin Meyer , Andrew David Deal , Mark Allen Cheverton , Samar Jyoti Kalita , Michael Francis Xavier Gigliotti
Abstract: The disclosure relates to an apparatus for manufacturing a metallic component, and corresponding methods. The apparatus may include a build plate with a build surface and an aperture. The apparatus may also include an actuator operable to translate a metallic component such that an end portion of the metallic component is positioned within the aperture of the build plate and below the build surface. The apparatus may further include a seal coupled within the aperture of the build plate and configured to engage the end portion of the metallic component. The aperture of the build plate, the seal, and the end portion of the metallic component may cooperate to form a powder bed to hold metallic powder therein. The apparatus may also include an external heat control mechanism operable to form a predetermined temperature profile of the end portion of the component to prevent cracking of the component.
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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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公开(公告)号：US10323532B2
公开(公告)日：2019-06-18
申请号：US15159678
申请日：2016-05-19
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Nicholas Joseph Kray , Narendra Digamber Joshi , Samar Jyoti Kalita , Paul Marsland , Wayne Spence
Abstract: The present disclosure generally relates to variable cellular structures, methods of making such cellular structures, and variable cellular flow discouragers for turbine engines for jet aircraft.
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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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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：US10920595B2
公开(公告)日：2021-02-16
申请号：US15405656
申请日：2017-01-13
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Narendra Digamber Joshi , Nicholas Joseph Kray , Samar Jyoti Kalita , Paul Marsland , Wayne Spence
IPC: F01D5/14 , B22F5/04 , F01D9/04 , F01D25/00 , B33Y10/00 , B22F3/105 , B23K26/342 , B23K26/082 , B33Y80/00 , B23K101/00 , B23K103/18
Abstract: The present disclosure generally relates to turbine engine components having multiple controlled metallic grain orientations. In general, the primary grain orientation is aligned substantially perpendicular to the longitudinal axis of the turbine engine component while the secondary grain orientation is aligned substantially parallel to the longitudinal axis. Such controlled grain orientations provide the blades and vanes with increased strength to withstand the thermal-mechanical stresses of the turbine operation. The disclosure also relates to turbines having these fortified components, and methods of manufacturing the components.
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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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