General Electric Company

Vishnu Das K

Atanu Saha

Manish Singhal

Ravindra Shankar Ganiger

Michael Anthony Thomas

Steven Mitchell Taylor

Scott Alan Schimmels

Sesha Subramanian

Kevin Lee Kirkeng

Reddi Hari Prasad Reddy Mylapalli

Jeffrey D Carnes

Carlos Ivan Flores

Vinaykumar Shrimantrao Patil

Sagar Pradhan

Fire retardant engine casing apparatus are disclosed. An example engine casing includes an inner shell circumferentially surrounding blades of a fan, a compressor, or a turbine, an outer shell positioned around the inner shell, and a fire retardant material between the inner shell and the outer shell.

Fire retardant engine casing apparatus

An example gas turbine engine includes a compressor including a casing defining a passageway and a shaft extending through the passageway. The shaft drivingly coupling the compressor and a turbine of the gas turbine engine. The shaft has an opening to receive airflow from the passageway. The gas turbine engine also includes an inner shroud, stator vanes coupled to and extending radially between the casing and the inner shroud, and an offtake scoop disposed on a downstream side of the inner shroud. The offtake scoop has a channel to direct the airflow radially inward toward the opening in the shaft.

Offtake scoops for bleed pressure recovery in gas turbine engines

An example compressor bleed slot apparatus includes an annular compressor casing, a blade row mounted for rotation about a centerline axis inside the compressor casing, a bleed slot passing through the forward section of the compressor casing, wherein the bleed slot is bounded by inboard and outboard walls defined within the compressor casing, the bleed slot extending along a slot axis, at least a portion of the bleed slot lying within an axial extent of the blade row, an array of struts interconnecting the inboard and outboard walls, and an annular supplemental flange extending radially outward from the forward section of the compressor casing, wherein at least a portion of the supplemental flange is axially positioned within an axial extent of the bleed slot, wherein the supplemental flange includes a necked-down portion adjacent the forward section of the compressor casing, the necked-down portion positioned axially between an inlet of the bleed slot and an outlet of the bleed slot.

Compressor apparatus with bleed slot and supplemental flange

Variable stator vanes with anti-lock trunnions are disclosed. An example apparatus disclosed herein includes an airfoil to be disposed within a flow path of a gas turbine engine, the gas turbine engine defining an axial axis, a radial axis and a circumferential axis, an outer trunnion, and an inner trunnion including a curved surface in an axial-radial plane, the inner trunnion enabling the airfoil to be rotatably mounted to an inner shroud of the gas turbine engine.

Variable stator vanes with anti-lock trunnions

Various embodiments include a compressor casing and a method of assembly. The compressor casing comprises a first and an adjacent, second annular casing segments each comprising an annular radially-extending flange with mounting holes; at least one annular recess disposed on at least one annular side mating face of the adjacent flanges of the adjacent segments; at least one set of stress-relief holes disposed through at least one flange of the adjacent segments; and at least one annular leak-resistant plate disposed within the at least one annular recess having at least a third set of mounting holes. All sets of mounting holes are substantially aligned with each other and receive a plurality of respective fasteners, and the at least one annular plate is clamped between the adjacent segments and seals the at least one set of stress-relief holes for preventing leakage therethrough.

High pressure compressor flow path flanges with leak resistant plates for improved compressor efficiency and cyclic life

A compressor bleed slot apparatus includes: an annular compressor casing; a stator vane row disposed inside the compressor casing; a blade row mounted for rotation about a centerline axis inside the compressor casing, axially downstream of the stator row; a bleed slot passing through the compressor casing, wherein the bleed slot is bounded by inboard and outboard walls defined within the compressor casing, the bleed slot having an inlet positioned axially between the stator vane row and the blade row, the bleed slot extending along a slot axis, at least a portion of the bleed slot lying within an axial extent of the blade row; an annular array of struts interconnecting the inboard and outboard walls; and an annular supplemental flange extending radially outward from the compressor casing, wherein at least a portion of the supplemental flange is axially positioned within an axial extent of the bleed slot.

Growing community of inventors

Bengaluru, India

Vishnu Das K