公开(公告)号：US20200378273A1

公开(公告)日：2020-12-03

申请号：US16424843

申请日：2019-05-29

Applicant: General Electric Company

Inventor： Abhijeet Jayshingrao Yadav ,  Nagamohan Govinahalli Prabhakar ,  Nicholas Joseph Kray ,  Shivam Mittal ,  Praveen Sharma ,  Bhujabal Prashant Mahadeo ,  Ravindra Shankar Ganiger

IPC: F01D25/24 ,  F01D25/00 ,  F02K3/06

Abstract: A composite fan casing for a gas turbine engine defining a central axis is generally provided. The composite fan casing includes a core having a plurality of core layers of reinforcing fibers bonded together with a thermosetting polymeric resin and having an outer surface. The composite fan casing further includes at least one stiffener integrally coupled to an aft portion of the outer surface of the core relative to the central axis. Additionally, the at least one stiffener comprises an elastic material.

公开(公告)号：US10703452B2

公开(公告)日：2020-07-07

申请号：US15295601

申请日：2016-10-17

Applicant: General Electric Company

Inventor： Nicholas Joseph Kray ,  Peggy Lynn Baehmann ,  Stefaan Guido Van Nieuwenhove

IPC: B63H1/20 ,  B63H1/26 ,  B63H1/28

Abstract: An apparatus and system for a marine propeller assembly are provided. An aft retention member that may be used with the marine propeller assembly includes a base, an opposing nose and a conic body extending therebetween along a centerline normal to the base. The aft retention member also includes at least one protuberance extending radially away from a surface of the conic body. The protuberance extends axially along a surface of the aft retention member from the base arcuately convergent to a predetermined point between the base and a tip of the nose.

公开(公告)号：US20200157953A1

公开(公告)日：2020-05-21

申请号：US16196288

申请日：2018-11-20

Applicant: General Electric Company

Inventor： Nitesh Jain ,  David William Crall ,  Nicholas Joseph Kray

IPC: F01D5/28 ,  F01D11/12

Abstract: A blade for a propulsion apparatus. The blade includes a body formed of a composite material and the body has opposed pressure and suction sides. The body extends in span between a root and a tip and extends in chord between a leading edge and a trailing edge. The body defines a body tip surface. A protective cover extends from near the tip of the blade toward the root of the blade along the leading edge and a trailing edge of the body. The protective cover defines a protective tip surface and an abrasive material is adhered to the protective tip surface.

公开(公告)号：US20200095883A1

公开(公告)日：2020-03-26

申请号：US16139645

申请日：2018-09-24

Applicant: General Electric Company

Inventor： Nicholas Joseph Kray ,  Nitesh Jain ,  Manoj Kumar Jain

IPC: F01D11/24 ,  F02C9/18 ,  F02C6/08 ,  F02K3/06

Abstract: A propulsion system including a casing surrounding a fan rotor assembly is provided. The casing includes an outer layer material defining a first coefficient of thermal expansion (CTE) and an inner layer material. The casing further includes a spring member disposed between the outer layer material and the inner layer material coupling the outer layer material and the inner layer material. The spring member is coupled to each of the outer layer material and the inner layer material within a flow passage defined between the outer layer material and the inner layer material. The spring member defines a second CTE greater than the first CTE.

公开(公告)号：US10450870B2

公开(公告)日：2019-10-22

申请号：US15018902

申请日：2016-02-09

Applicant: General Electric Company

Inventor： Phani Nandula ,  Suresh Subramanian ,  Nicholas Joseph Kray ,  Gregory Carl Gemeinhardt

IPC: F01D5/14 ,  F02C3/06

Abstract: An airfoil for an aircraft engine is provided. The airfoil may include a plurality of composite plies extending in a chordwise direction from a leading edge to a trailing edge and in a spanwise direction between an airfoil tip and an airfoil base. The airfoil may include at least one discontinuous ply having a first ply segment, a second ply segment, and a butt joint disposed between the first ply segment and the second ply segment. The butt joint may be disposed along a first fragment profile to frangibly attach the first and second ply segments.

公开(公告)号：US10422348B2

公开(公告)日：2019-09-24

申请号：US15402536

申请日：2017-01-10

Applicant: General Electric Company

Inventor： Nicholas Joseph Kray ,  Daniel Edward Mollmann ,  Andrew Breeze-Stringfellow

IPC: F04D29/52 ,  F01D21/04 ,  F02C7/04 ,  F04D29/38 ,  F02K3/06

Abstract: A containment structure comprising an annular structure configured to provide close tolerance to a rotation structure. The containment structure includes a first abradable structure, a second abradable structure, and a shroud that is defined in part by the first abradable structure and in part by the second abradable structure. An annular surface of the shroud is defined by the first abradable structure and by the second abradable structure. The first abradable structure is harder than the second abradable structure.

公开(公告)号：US10422340B2

公开(公告)日：2019-09-24

申请号：US15308968

申请日：2015-05-06

Applicant: General Electric Company

Inventor： Nicholas Joseph Kray ,  Suresh Subramanian ,  Phani Nandula ,  Dong-Jin Shim ,  Todd Alan Anderson ,  Mark Ernest Vermilyea

IPC: F04D29/02 ,  F01D5/06 ,  F01D5/30 ,  F04D29/32 ,  F01D5/28 ,  F04D29/64

Abstract: According to present embodiments or aspects thereof, a composite booster spool with separable composite blades is provided. The blades are inserted radially from within the inner circumference of the spool and extend outwardly through the spool. The system provides a reduced weight assembly as compared to prior art metallic or composite/metallic combination systems. Additionally, the blades are separable which results in a more field-serviceable assembly over a fully integral system wherein the blades and spool are integrally formed from composites or combination of metal and composites.

公开(公告)号：US20190226402A1

公开(公告)日：2019-07-25

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 ,  F01D25/02 ,  B64D33/02

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.

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

IPC: F01D11/08 ,  F01D11/12 ,  F16J15/44 ,  F01D11/02

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.

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.