公开(公告)号：US11674399B2

公开(公告)日：2023-06-13

申请号：US17368961

申请日：2021-07-07

Applicant: General Electric Company

Inventor： Ravindra Shankar Ganiger ,  Praveen Sharma ,  Abhijeet Jayshingrao Yadav ,  Nitesh Jain ,  Nicholas Joseph Kray

IPC: F01D5/28 ,  F01D5/14 ,  F01D5/30

CPC classification number: F01D5/282 ,  F01D5/147 ,  F01D5/30 ,  F05C2251/08 ,  F05D2240/303 ,  F05D2240/304 ,  F05D2240/307 ,  F05D2300/505

Abstract: An airfoil arrangement for a gas turbine engine may include a support device using a shape memory alloy to support and control the airfoil. The support device may be formed as part of a fan blade. The arrangement may be configured to reduce overall weight and dimensions of the gas turbine engine.

公开(公告)号：US11674395B2

公开(公告)日：2023-06-13

申请号：US17024212

申请日：2020-09-17

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Nicholas Joseph Kray ,  Nitesh Jain

IPC: F01D5/08 ,  B33Y80/00 ,  B23P6/00

CPC classification number: F01D5/08 ,  B23P6/007 ,  B33Y80/00

Abstract: A rotor disk for a gas turbine engine includes a disk body having a central bore extending therethrough. The disk body includes a bore body that extends around the central bore, a web that extends radially outward from the bore body having decreased thickness relative to the bore body and a peripheral rim that is located at an outer end of the web. The peripheral rim includes blade mounting structures for engaging complementary mounting structures of rotor blades. The bore body has a bore cavity that extends continuously through the bore body and about an entire periphery of the central bore. The bore cavity has a central axis that forms a circle about the central bore.

公开(公告)号：US20230036022A1

公开(公告)日：2023-02-02

申请号：US17488836

申请日：2021-09-29

Applicant: General Electric Company

Inventor： Nicholas Joseph Kray ,  Nitesh Jain

IPC: F01D5/14 ,  F02K3/06

Abstract: A rotor blade for a gas turbine engine is provided. The rotor blade includes a blade body formed of a first material; and a spar within a portion of the blade body, the spar formed of a second material that is different than the first material, the spar having an elongate body including a notch. The notch, weakened geometric feature, or other reduction in cross-section defines a frangible portion of the spar that is used to control a fracture of a rotor blade.

公开(公告)号：US20230029918A1

公开(公告)日：2023-02-02

申请号：US17490401

申请日：2021-09-30

Applicant: General Electric Company

Inventor： Abhijeet Jayshingrao Yadav ,  Nitesh Jain ,  Nicholas Joseph Kray

IPC: F01D5/14 ,  F03G7/06

Abstract: An airfoil including a plurality of composite plies extending from a leading edge to a trailing edge and between a tip and a root. The airfoil further includes a frangible airfoil portion at the tip extending between the leading edge and the trailing edge and extending between the tip and a frangible line along a span. The frangible airfoil portion including a plurality of composite plies and one or more shape memory alloy inserts disposed between the plurality of composite plies. A gas turbine engine including a frangible airfoil and methods for forming a frangible airfoil are also disclosed.

公开(公告)号：US11286807B2

公开(公告)日：2022-03-29

申请号：US16145656

申请日：2018-09-28

Applicant: General Electric Company

Inventor： Nitesh Jain ,  Abhijit Roy ,  Kishore Budumuru ,  Nicholas Joseph Kray

IPC: F01D21/04 ,  F01D5/14

Abstract: A blade for a propulsion apparatus that includes a body formed of a first material having opposed pressure and suction sides, and extending in span between a root and a boundary, and extending in chord between a leading edge and a trailing edge. A tip region that is formed of a second material and that is positioned such that it extends from the body and defines a tip. The tip region joins the body at the boundary. The tip region is configured to fail when a predetermined force is applied to the tip such that the tip separates from the blade and defines a fused tip.

公开(公告)号：US20220074344A1

公开(公告)日：2022-03-10

申请号：US17365855

申请日：2021-07-01

Applicant: General Electric Company

Inventor： Nicholas Joseph Kray ,  Sreekanth Kumar Dorbala ,  Nitesh Jain ,  Prashant Sharma

IPC: F02C7/047 ,  B64D33/02 ,  F01D25/02

Abstract: A booster splitter for a gas turbine engine and a method of additively manufacturing the booster splitter are provided. The booster splitter includes an annular inner wall defining a radially outer boundary of a compressor flow path defined through a compressor section of the gas turbine engine, an annular outer wall spaced apart from the annular inner wall along the radial direction, the annular outer wall adjacent to the annular inner wall at a forward end, the forward end defining an inlet to the compressor flow path, an annular bulkhead spanning between the annular inner wall and the annular outer wall substantially along the radial direction, the bulkhead defining an inlet port, and a passageway defined within the annular outer wall, the passageway extending from the inlet port, into the bulkhead, radially outward to the outer wall, and through the annular outer wall towards the inlet defined by the forward end.

公开(公告)号：US11261753B2

公开(公告)日：2022-03-01

申请号：US15832814

申请日：2017-12-06

Applicant: General Electric Company

Inventor： Abhijeet Jayshingrao Yadav ,  Nicholas Joseph Kray ,  Nitesh Jain ,  Saurabh Sanjay Rasal

IPC: F01D21/08 ,  F02K3/06 ,  F02C7/36 ,  F01D25/16 ,  F16D3/18 ,  F16D1/10 ,  F02C3/107 ,  F02C7/06

Abstract: A rotor assembly includes a fan rotor shaft coupled to a fan rotor, a low pressure turbine rotor shaft coupled to a low pressure turbine rotor, and a joint device configured to connect the fan rotor shaft to the low pressure turbine rotor shaft, to allow torsion, shear and bending to be transferred between the fan rotor shaft and the low pressure turbine rotor shaft under normal operation, and allow torsion and shear but prevent bending to be transferred between the fan rotor shaft and the low pressure turbine rotor shaft under a fan blade-out event.

公开(公告)号：US20220034331A1

公开(公告)日：2022-02-03

申请号：US17502620

申请日：2021-10-15

Applicant: General Electric Company

Inventor： Nitesh Jain ,  Sujana Chandrasekar ,  Ramkrishna Maripalli ,  Nicholas Joseph Kray ,  Wendy Wenling Lin

IPC: F04D29/38 ,  B32B5/02 ,  F02C3/04 ,  F04D29/32 ,  F02K3/06 ,  F04D29/02 ,  B29C70/02 ,  F01D5/28 ,  B32B37/14 ,  B29C70/20

Abstract: A laminated composite airfoil assembly includes a first lamina formed of a material including metal fibers, and at least a second lamina formed of a material including at least one of metal fibers intermixed with carbon fibers, only metal fibers, only carbon fibers, a substrate including metal fibers, a substrate including carbon fibers, and combinations thereof.

公开(公告)号：US11156099B2

公开(公告)日：2021-10-26

申请号：US15471729

申请日：2017-03-28

Applicant: General Electric Company

Inventor： Nitesh Jain ,  Abhijeet Jayshingrao Yadav ,  Kishore Budumuru ,  Nicholas Joseph Kray

IPC: F01D5/14 ,  F15D1/00 ,  F01D25/02 ,  F01D17/16

Abstract: A turbine engine can comprise a fan section, compressor section, a combustion section, and a turbine section in axial flow arrangement. At least one of the fan section and compressor section can include an airfoil with a leading edge, and a plurality of riblets can be arranged on the leading edge.

公开(公告)号：US11053848B2

公开(公告)日：2021-07-06

申请号：US15878759

申请日：2018-01-24

Applicant: General Electric Company

Inventor： Nicholas Joseph Kray ,  Sreekanth Kumar Dorbala ,  Nitesh Jain ,  Prashant Sharma

IPC: F02C7/047 ,  B64D33/02 ,  F01D25/02

Abstract: A booster splitter for a gas turbine engine and a method of additively manufacturing the booster splitter are provided. The booster splitter includes an annular outer wall defining an internal fluid passageway in fluid communication with a fluid supply and terminating in discharge ports that eject a flow of fluid into the compressor section of the gas turbine engine. The internal fluid passageway may also be in fluid communication with heating plenums of a first plurality of airfoils for heating those airfoils.