-
公开(公告)号：US11111815B2
公开(公告)日：2021-09-07
申请号：US16161253
申请日：2018-10-16
Applicant: General Electric Company
Inventor： Nicholas Joseph Kray , Nitesh Jain , Daniel Edward Mollmann
Abstract: An airfoil defining a span extending between a root and a tip and a chord at each point along the span extending between a leading edge and a trailing edge. The airfoil 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 the span. The frangible airfoil portion includes an exterior surface. The exterior surface at least partially defines at least one fusion cavity at least partially defining the frangible line. The airfoil further includes a residual airfoil portion extending from the frangible line to the root along the span. The residual airfoil portion meets the frangible airfoil portion at the frangible line. As such, the frangible airfoil portion deforms or partially or fully detaches relative to the residual airfoil portion at the frangible line following an event creating imbalance.
-
公开(公告)号：US10801361B2
公开(公告)日：2020-10-13
申请号：US15260641
申请日：2016-09-09
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Nagamohan Govinahalli Prabhakar , Steven Andrew Strang , Charles Stanley Orkiszewski , Subramanya Shankar , Nitesh Jain , Michael Riehle
Abstract: The turbine assembly includes a shaft, a plurality of rotor disks, a plurality of blades, and at least one cutting mechanisms. The rotor disks are spaced axially along, and coupled to, the shaft and include a radially outer portion. The blades are spaced circumferentially around the radially outer portion. The cutting mechanisms are configured to cut the blades from the rotor disk during a disk over speed condition.
-
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
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
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：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
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.
-
Patent Agency Ranking
公开(公告)号：US20180334922A1
公开(公告)日：2018-11-22
申请号：US15596523
申请日：2017-05-16
Applicant: General Electric Company
Inventor： Nicholas Joseph Kray , Thomas Chadwick Waldman , Manoj Kumar Jain , Mojibur Rahman , Nitesh Jain , Nagamohan Govinahalli Prabhakar , Scott Roger Finn , Apostolos Pavlos Karafillis
CPC classification number: F01D21/045 , F01D25/24 , F02C3/04 , F02K3/06 , F05D2220/323 , F05D2240/14 , F05D2300/501
Abstract: A softwall containment system for a machine includes an inner wall circumscribing a bladed rotatable member of the machine and extending from a forward end to an aft end. The softwall containment system also includes an outer wall circumscribing the inner wall and extending from a forward end to an aft end. The outer wall is spaced radially outwardly from the inner wall. The outer wall extends axially between a first joint coupling the forward end of the inner wall to the forward end of the outer wall and a second joint coupling the aft end of the inner wall to the aft end of the outer wall. The softwall containment system also includes an anti-ballistic material wrap covering the outer wall, the anti-ballistic material wrap including at least one of a first extension extending forward of the first joint and a second extension extending aft of the second joint.
-
公开(公告)号：US20180073388A1
公开(公告)日：2018-03-15
申请号：US15260641
申请日：2016-09-09
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Nagamohan Govinahalli Prabhakar , Steven Andrew Strang , Charles Stanley Orkiszewski , Subramanya Shankar , Nitesh Jain , Michael Riehle
Abstract: The turbine assembly includes a shaft, a plurality of rotor disks, a plurality of blades, and at least one cutting mechanisms. The rotor disks are spaced axially along, and coupled to, the shaft and include a radially outer portion. The blades are spaced circumferentially around the radially outer portion. The cutting mechanisms are configured to cut the blades from the rotor disk during a disk over speed condition.
-
公开(公告)号：US20170191493A1
公开(公告)日：2017-07-06
申请号：US14985169
申请日：2015-12-30
Applicant: General Electric Company
Inventor： Nicholas Joseph Kray , Jan Christopher Schilling , Nitesh Jain , Abhijit Roy
CPC classification number: F04D29/324 , F01D5/147 , F01D5/282 , F01D5/30 , F01D11/008 , F04D29/023 , F04D29/322 , F05D2220/32 , F05D2230/20 , F05D2230/23 , F05D2230/60 , F05D2240/30 , F05D2240/80 , F05D2260/30 , F05D2300/603 , Y02T50/672 , Y02T50/673
Abstract: A composite blade assembly and a method of assembling a composite blade are provided. The composite blade assembly includes a composite blade having a radially inner root. A composite blade assembly includes a first platform and a circumferentially adjacent second platform abutting the first platform at a platform joint. Each of the first platform and the second platform includes a radially outer surface and a radially inwardly extending attachment member. The platform joint includes a slot extending through adjacent edges of the first platform and the second platform. The slot is configured to receive the radially inner root and the radially inner root is configured to be sandwiched between the attachment members. The blade assembly includes an adhesive system configured to join the radially inner root of the composite blade and the attachment members into a unitary structure, and a retaining clip configured to bias the attachment members towards each other.
-
公开(公告)号：US20250059894A1
公开(公告)日：2025-02-20
申请号：US18476474
申请日：2023-09-28
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Abhijeet Jayshingrao Yadav , Frank Worthoff , Nicholas Joseph Kray , Nitesh Jain , Balaraju Suresh
Abstract: A turbine engine including a fan section, a compressor section, a combustion section, and a turbine section in serial flow arrangement. The turbine engine further including a composite airfoil assembly. The composite airfoil assembly having an outer wall, a composite body at least partially defining the outer wall, and a tip cap at least partially defining the outer wall.
-
公开(公告)号：US20240141790A1
公开(公告)日：2024-05-02
申请号：US18154556
申请日：2023-01-13
Applicant: General Electric Company
Inventor： Abhijeet Yadav , Kishore Budumuru , Nitesh Jain
CPC classification number: F01D5/147 , F01D5/286 , F02C7/20 , F05D2240/307 , F05D2300/17 , F05D2300/505
Abstract: Methods, apparatus, systems, and articles of manufacture are disclosed for passive fan blade tip clearance control. A fan blade for a gas turbine engine, the fan blade comprising a fan blade body including a tip region at a blade tip of the fan blade body and a blade tip insert disposed within the tip region of the fan blade body, the blade tip insert is formed from a material that passively adjusts a shape of the blade tip insert to maintain a blade tip clearance between the blade tip and an engine casing or nacelle by at least one of expanding or contracting based on temperature.
-
-
-
-
-
-
-
-
-
Search Results
109
records
(took 0.02 seconds)
