General Electric Company

Unison Industries, Inc.

Sheo Narain Giri

Harish Bommanakatte

Shiloh Montegomery Meyers

Brian Christopher Kemp

Pallavi Tripathi

Sanjeev Kumar Jha

Bhaskar Pemmi

Nagendra Baddam

Ravindra Shankar Ganiger

David Raju Yamarthi

Jonathan Matthew Lomas

Brad Wilson Vantassel

John Carl Glessner

John David Ward, Jr

Rajarshi Saha

Spencer Aaron Kareff

David Randolph Spracher

Zachary James Taylor

Indrajit Mazumder

Siddaraja Mallikarjuna Devangada

Santhosh Donkada

Gayathri Puram

Debdulal Das

Ryan Zane Ziegler

Mohankumar Banakar

Saurya Ranjan Ray

Krishna Kishore Gumpina

Rajesh Achudhan

A turbine engine having an engine core having a compression section, combustion section, a turbine section, and an engine drive shaft. The turbine engine includes an air turbine starter having a housing defining an air flow passage. The air turbine starter can operate in a start-up mode and a shut-down mode. The turbine engine further includes a gearbox and a drive unit.

Turbine engine including an air turbine starter

A turbine engine including an engine core, an engine drive shaft, an accessory gear box (AGB), an air turbine starter (ATS), and a bleed air circuit. The engine core has a fan section, a compressor section, a combustion section, and a turbine section in serial flow arrangement. The engine drive shaft operably couples the fan section, the compressor section, and the turbine section. The AGB and the ATS are operably coupled to the engine drive shaft.

Turbine engine including an air turbine starter and a bleed air circuit

A turbine engine including an engine core, an engine drive shaft, an accessory gear box (AGB), an air turbine starter (ATS) and a bleed air circuit. The engine core has a fan section, a compressor section, a combustion section, and a turbine section in serial flow arrangement. The engine drive shaft operably couples the fan section, the compressor section and the turbine section. The AGB and the ATS are operably coupled to the engine drive shaft.

A damper pin for damping adjacent turbine blades coupled to a rotor shaft includes an elongated body having a center portion that is disposed between a first end portion and a second end portion. The first end portion, center portion and second end portion at least partially define a generally arcuate top portion of the elongated body. At least a portion of the top portion may be configured to contact with a groove that is defined between the adjacent turbine blades. The first end portion and the second end portion have substantially semi-cylindrical cross sectional shapes and the center portion has a cylindrical cross sectional shape. A bottom portion of the elongated body diverges radially outwardly from the first end portion to the center portion and from the second end portion to the center portion.

Variable cross-section damper pin for a turbine blade

A turbine bucket adapted to be supported on a turbine or rotor wheel includes an airfoil portion extending radially relative to a longitudinal axis of the rotor wheel and having a leading edge, a trailing edge, a pressure side and a suction side. At least one tip shroud extends in opposite circumferential directions, the shroud having a first hard face adapted to engage a mating second hard face on a shroud extending circumferentially from an adjacent bucket. The first hard face defined by a surface portion that varies circumferentially with an increasing radius as measured from the longitudinal axis of the rotor wheel.

Turbine blade tip shroud and mid-span snubber with compound contact angle

A cooling arrangement for a gas turbine engine. The cooling arrangement comprises a discharge channel for air flow from a compressor, a first cooling channel and at least one aperture providing communication between the flow of air through the discharge channel and the first cooling channel. A restrictor device in the aperture regulates the flow of air between the discharge channel and the first cooling channel. The restrictor device deforms to vary air flowing through the aperture in response to a physical condition of the engine. This physical condition of the engine may be that of the temperature of air flowing through the discharge channel, the restrictor device responding to regulate the flow of air based on that temperature. The restrictor device may be a two-way shape memory alloy.

Part load performance improvement using deformable bore plugs

Embodiments of the present application include a gas turbine system. The system may include a rotor wheel and one or more impeller vanes radially disposed on the rotor wheel. The system may also include one or more fluid passages defined by adjacent impeller vanes. The one or more fluid passages may be radially disposed across the rotor wheel. Moreover, the system may include one or more shape memory alloy valves disposed within each of the fluid passages. The one or more shape memory alloy valves may be configured to change shape to control a flow of fluid through the fluid passages.

Systems and methods to control flow in a rotor wheel

A turbomachine system includes a turbomachine that includes a rotor that includes a rotational axis, a first rotating segment having a first mating axial mount coupled to a first axial mount of the rotor in a first installed position and a first pin configured to insert into a first inserted position in both a first slot in the rotor and a first mating slot in the first rotating segment. The first pin in the first inserted position is configured to block axial movement of the first mating axial mount relative to the first axial mount. The turbomachine also includes a second rotating segment having a second mating axial mount coupled to a second axial mount of the rotor in a second installed position. The second rotating segment in the second installed position is configured to block removal of the first pin.

System for axial retention of rotating segments of a turbine

A rotating airfoil component of a turbomachine, in which the component has an airfoil aligned in a spanwise direction of the component, a shank, and a platform therebetween oriented transverse to the spanwise direction. The platform has an outer radial surface adjacent the airfoil, and at least one recessed region defined in its outer radial surface. The recessed region extends opposite the spanwise direction from a platform plane that contains portions of the outer radial surface that are upstream and downstream from the recessed region. The recessed region is contiguous with an end wall of the platform and extends therefrom toward the airfoil. The recessed region defines a surface shape whose boundary is contained by the platform plane, and has a profile shape that extends from the end wall toward the airfoil. The recessed region is sized and shaped to increase the stiffness of the platform.

Rotating airfoil component with platform having a recessed surface region therein

An impingement plate adapted to reduce thermally-induced strains and stresses that may damage the plate or its attachment to a second component. The plate includes an interior region having cooling holes, a peripheral wall surrounding the interior region and projecting out of the plane of the interior region, a peripheral flange surrounding the peripheral wall and lying in a plane spaced apart from the plane of the interior region, and one or more through-thickness rib. One such rib may be disposed in the interior region, project away from and out of the plane of the interior region, and linearly extend across the interior region. Alternatively or in addition, one such rib may be disposed between the peripheral wall and flange and project out of the plane of the flange.

Impingement plate for turbomachine components and components equipped therewith

A torsion seal is provided and includes a first section, a second section and a torsion section connected at opposite end portions thereof to the first and second sections and having a central portion extending between the opposite end portions to absorb differential thermal growth of vessels to which the first and second sections are coupled.

Torsion seal

A turbine bucket for a gas turbine engine is described herein. The turbine bucket may include an airfoil, a tip shroud positioned on a tip of the airfoil, and a number of cooling holes extending through the airfoil and the tip shroud. One or more of the cooling holes may include a length of narrowing diameter about the tip shroud and a length of expanding diameter about a surface of the tip shroud.

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Bengaluru, India

Sheo Narain Giri