公开(公告)号：US10704414B2

公开(公告)日：2020-07-07

申请号：US15455710

申请日：2017-03-10

Applicant: General Electric Company

Inventor： Nitesh Jain ,  Nicholas Joseph Kray ,  Manoj Kumar Jain ,  Mojibur Rahman ,  Nagamohan Govinahalli Prabhakar ,  Scott Roger Finn ,  Thomas Chadwick Waldman ,  Apostolos Pavlos Karafillis

IPC: F01D21/04

Abstract: A containment structure for surrounding a rotatable machine includes a double-walled inner shell having a forward end, an aft end, and a substantially cylindrical body extending therebetween. The inner shell includes an inner wall at least partially surrounding a bladed portion of the bladed rotor, and an outer portion that branches radially outward from the inner wall. The containment structure also includes a substantially cylindrical back sheet coupled to the outer portion and disposed radially outward of the inner wall.

公开(公告)号：US20180258796A1

公开(公告)日：2018-09-13

申请号：US15455710

申请日：2017-03-10

Applicant: General Electric Company

Inventor： Nitesh Jain ,  Nicholas Joseph Kray ,  Manoj Kumar Jain ,  Mojibur Rahman ,  Nagamohan Govinahalli Prabhakar ,  Scott Roger Finn ,  Thomas Chadwick Waldman ,  Apostolos Pavlos Karafillis

IPC: F01D25/26 ,  F01D5/02 ,  F02K3/06 ,  F04D19/00 ,  F04D29/52

Abstract: A containment structure for surrounding a rotatable machine includes a double-walled inner shell having a forward end, an aft end, and a substantially cylindrical body extending therebetween. The inner shell includes an inner wall at least partially surrounding a bladed portion of the bladed rotor, and an outer portion that branches radially outward from the inner wall. The containment structure also includes a substantially cylindrical back sheet coupled to the outer portion and disposed radially outward of the inner wall.

公开(公告)号：US20180238346A1

公开(公告)日：2018-08-23

申请号：US15438284

申请日：2017-02-21

Applicant: General Electric Company

Inventor： Veeraraju Vanapalli ,  Nitesh Jain ,  Viswanadha Gupta Sakala ,  Bhaskar Nanda Mondal ,  Nicholas Joseph Kray

IPC: F04D29/52 ,  F04D19/00 ,  F04D29/32 ,  F04D29/02

Abstract: A turbine engine that includes a rotor assembly including a plurality of rotor blades, an outer case positioned radially outward from the plurality of rotor blades, and an annular ring coupled to the outer case and positioned between the plurality of rotor blades and the outer case. The annular ring is configured to restrict thermal contraction of the outer case towards the plurality of rotor blades.

公开(公告)号：US09976429B2

公开(公告)日：2018-05-22

申请号：US14734091

申请日：2015-06-09

Applicant: General Electric Company

Inventor： Nicholas Joseph Kray ,  Baskaran Bhuvaraghan ,  Nitesh Jain

IPC: F01D5/30 ,  B29C70/34 ,  B29D99/00 ,  B29C70/48 ,  F01D5/02 ,  F01D5/28

CPC classification number: F01D5/3023 ,  B29C70/345 ,  B29C70/48 ,  B29D99/0025 ,  F01D5/028 ,  F01D5/282 ,  F01D5/3007 ,  F05D2220/36

Abstract: A gas turbine engine composite disk includes dovetail slots between disk posts extending radially inwardly from a periphery, a hub ring of composite plies circumscribed about a centerline axis, and radial plies extending radially away from hub ring into disk posts. A segmented intermediate ring concentric with and located radially outwardly of hub ring includes intermediate ring segments having nested plies with annular bases circumscribed about centerline axis and substantially radially extending clockwise and counter-clockwise radial ply arms. An outer segmented ring may be concentric with and located radially outwardly of intermediate ring, include annular outer ring segments with circumferentially stacked composite plies disposed within intermediate ring segments between clockwise and counter-clockwise radial ply arms and radially outwardly of annular bases. An outer skin of outermost composite covering plies may extend circumferentially around composite disk. Circumferential and radial composite plies may include circumferentially and radially oriented fibers.

公开(公告)号：US20180080339A1

公开(公告)日：2018-03-22

申请号：US15705712

申请日：2017-09-15

Applicant: General Electric Company

Inventor： Nicholas Joseph Kray ,  Benjamin James Roby ,  Vijesh Shetty Anangoor ,  Nitesh Jain ,  Sreekanth Kumar Dorbala ,  Nagamohan Govinahalli Prabhakar ,  K Phani SriKrishna Chinnapragada

IPC: F01D21/04

CPC classification number: F01D21/045 ,  F01D25/24 ,  F02C7/04 ,  F05D2250/182 ,  F05D2250/232 ,  F05D2250/283 ,  F05D2300/603 ,  Y02T50/672

Abstract: Fan blade containment system includes a composite fan case with an annular composite shell extending from forward flange downstream to aft flange, and circumferentially varying thickness portion of composite shell. Annular composite back sheet spaced radially outwardly of annular composite shell has annular filler layer disposed radially therebetween. Annular forward and aft seams between annular composite shell and composite back sheet may axially trap filler layer. Circumferentially varying thickness portion may include aftwardly extending fingers of composite back sheet in aft seam and first thickness of fingers thicker than second thickness of composite shell circumferentially between fingers. Composite shell may extend from forward flange to aft flange. Aft flange bolted to metallic flange of metallic fan casing aft of aft flange. Containment system may circumscribe and surround fan and fan blades of gas turbine engine fan section.

公开(公告)号：US20250084771A1

公开(公告)日：2025-03-13

申请号：US18492837

申请日：2023-10-24

Applicant: GENERAL ELECTRIC COMPANY

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

IPC: F01D17/16

Abstract: A turbine engine comprising a fan section, a compressor section, a combustion section, and a turbine section in serial flow arrangement and defining a stator portion and a rotor portion, which rotates about an engine centerline. The rotor portion comprising a variable pitch airfoil assembly. The variable pitch airfoil assembly having an airfoil and a balancing insert.

公开(公告)号：US12055054B2

公开(公告)日：2024-08-06

申请号：US17234371

申请日：2021-04-19

Applicant: General Electric Company

Inventor： Nitesh Jain ,  Nicholas J. Kray ,  Veeraraju V ,  Deepak Ghiya ,  Sreekanth Kumar Dorbala ,  Kishore Budumuru ,  Apostolos Karafillis ,  Thomas Chadwick Waldman ,  Theodore E Anderson ,  Joel F. Kirk ,  Edward A. Rainous ,  Michael E Eriksen ,  Mojibur Rahman

IPC: F01D21/04 ,  F01D25/24

CPC classification number: F01D21/045 ,  F01D25/24 ,  F05D2220/36 ,  F05D2240/20

Abstract: Light weight fan casing configurations for energy absorption are disclosed herein. An apparatus includes a first set of metal bands positioned within a containment casing of a turbofan engine, and a second set of metal bands traversing the first set of metal bands, the first set of metal bands and the second set of metal bands to surround at least a portion of the turbofan engine.

公开(公告)号：US20240076989A1

公开(公告)日：2024-03-07

申请号：US18081151

申请日：2022-12-14

Applicant: General Electric Company

Inventor： David Raju Yamarthi ,  Ravindra Shankar Ganiger ,  Vasanth Kumar Balaramudu ,  Vishnu Vardhan Venkata Tatiparthi ,  Nitesh Jain ,  Vidyashankar Ramasastry Buravalla

IPC: F01D5/14

CPC classification number: F01D5/147 ,  F05D2230/60

Abstract: An airfoil assembly extends along a radial direction between a root and a tip, the airfoil assembly comprising: a first blade segment positioned proximate the root of the airfoil assembly; a second blade segment positioned adjacent the first blade segment along the radial direction; and a tensioning assembly comprising a plurality of tensioning strings that extend between and mechanically couple the first blade segment and the second blade segment.

公开(公告)号：US20240052748A1

公开(公告)日：2024-02-15

申请号：US18494485

申请日：2023-10-25

Applicant: General Electric Company

Inventor： Nicholas J. Kray ,  Gary W. Bryant ,  Nitesh Jain

IPC: F01D5/16 ,  F02C7/00 ,  F01D25/04 ,  F01D25/06 ,  F01D5/26

CPC classification number: F01D5/16 ,  F02C7/00 ,  F01D25/04 ,  F01D25/06 ,  F01D5/26 ,  F05D2300/603 ,  F05D2260/96 ,  F05D2220/32

Abstract: Methods and apparatus to reduce deflection of an airfoil are disclosed. An example apparatus disclosed herein includes a plate including an aperture, the airfoil disposed in the aperture, and a damper operatively coupled between the plate and a hub of the airfoil, the damper to transform flexural deflection of the airfoil to radial deflection of the plate.

公开(公告)号：US11692444B2

公开(公告)日：2023-07-04

申请号：US17891312

申请日：2022-08-19

Applicant: General Electric Company

Inventor： Nicholas Joseph Kray ,  Nitesh Jain

IPC: F01D5/02

CPC classification number: F01D5/028

Abstract: A rotor blade for a gas turbine engine includes an airfoil section and a root section extending along a longitudinal direction between an upstream surface and a downstream surface. The root section further extends along a radial direction between an inner surface positioned at an inner end of the root section and an outer end coupled to the airfoil section. Moreover, the root section extends along a circumferential direction between a first side surface and a second side surface. Furthermore, the root section defines a longitudinal centerline extending along the longitudinal direction and positioned equidistant from the inner surface and the outer end in the radial direction. The root section includes a first portion formed from a composite material and a second portion formed from a metallic material, with the longitudinal centerline extending through the second portion of the root section.