General Electric Company

Dennis Paul Dry

Daniel Patrick Kerns

Mark Eugene Noe

Brandon ALlanson Reynolds

Jon Conrad Schaeffer

Christopher Edward Wolfe

Richard William Albrecht, Jr

Jason David Shapiro

Robert J Corsmeier

Andres Jose Garcia-Crespo

Jeffrey Allen Conner

Matthew Mark Weaver

Jinjie Shi

Alexander Martin Sener

Robert Randolph Berry

Wei Ning

Mullahalli Venkataramaniah Srinivas

Alan R Gilchrist

Megan Elizabeth Scheitlin

Todd William Bachmann

Ronald E Schlechtweg

Gregory J Anselmi

Yun Zhu

Edward M Duran

David C Zigan

A flow path assembly for a gas turbine engine is provided. The flow path assembly may include an outer casing comprising a metal material having a first coefficient of thermal expansion, a ceramic structure comprising a ceramic material having a second coefficient of thermal expansion, and a mounting component attached on a first end to the outer casing and attached on a second end to the ceramic structure. The mounting component may be constructed from at least two materials transitioning from the first end to the second end such that the coefficient of thermal expansion is different at the first end than the second end.

CTE matching hanger support for CMC structures

An airfoil assembly for a turbine engine defines an axial direction, a radial direction, and a circumferential direction, and includes a first airfoil defining a first end along the radial direction, a first hub disposed on the first end of the first airfoil and having a first extension member extending at least partially in the radial direction, and a second airfoil adjacent to the first airfoil, the second airfoil defining a first end along the radial direction, a second hub disposed on the first end of the second airfoil and comprising a second extension member extending at least partially in the radial direction, and a circumferential bias assembly operable with the first extension member, the second extension member, or both for exerting a circumferential force on the first extension member, the second extension member, or both.

Airfoil assembly

A shroud assembly includes a shroud segment and a hanger. In one exemplary aspect, the shroud segment has a shroud body extending substantially along a circumferential direction between a first end and a second end. The shroud body defines a radial centerline along the circumferential direction. A flange is attached to or integral with the shroud body. The flange is pivotally coupled with the hanger at a location spaced from the radial centerline of the shroud body.

Aero loading shroud sealing

Coating systems for a cooled turbine blade tip, such as a metal turbine blade tip, are provided. The coating system includes an abrasive layer overlying the surface of the turbine blade tip. One or more buffer layers may additionally be disposed between an outer surface of the blade tip and the abrasive layer. The coated blade tip can be used with a ceramic matrix composite (CMC) shroud coated with an environmental barrier coating (EBC) to provide improved cooling to the tip so as to lengthen oxidation time of the abrasive layer and reduce blade tip wear. Methods are also provided for forming the cooled blade tip and applying the coating system onto the cooled turbine blade tip.

Turbine blade and method of forming blade tip for eliminating turbine blade tip wear in rubbing

In one aspect the present subject matter is directed to a system for cooling a turbine engine. The system includes a cooling medium source, a stator vane having an internal flow passage that is in fluid communication with the cooling medium source and a turbine shroud assembly having an internal flow passage that is in fluid communication with the internal flow passage of the stator vane. The system allows for reduced peak thermal gradients between a cooling medium provided by the cooling medium source and various turbine hardware components such as the turbine shroud assembly.

System for cooling a turbine engine

A method for removing an environmental coating on an article intended for use in a hostile environment, such as turbine, combustor and augmentor components of a gas turbine engine. The method is particularly suited for the repair of diffusion aluminide coatings covered by a protective oxide scale, which may further include a thermal insulating ceramic outer layer. Processing steps generally include peening the environmental coating at a temperature below the ductile-to-brittle transition temperature of the diffusion coating, such that cracks are formed in the diffusion coating. Thereafter, the diffusion coating is subjected to an acidic solution that penetrates the cracks and interacts with the coating diffusion zone, resulting in the diffusion coating being chemically stripped from its underlying substrate.

Method for removing an environmental coating

The present invention provides a rotor blade capable of being axially loaded in slots on a gas turbine engine rotor and particularly suited for use on turbine disks. The blade has a generally axially extending dovetail root which is effective for being loaded into a rotor disk slot between adjacent disk posts. Anti-rock tangs are disposed radially outward of the root and tangentially extend from the shank and are generally linear in the axial direction. The anti-rock tangs are effective to engage the radially outwardmost facing surfaces of the adjacent dovetail posts between which is disposed the associated dovetail slot.

Anti-rock blade tang

A boltless blade retainer for preventing forward axial movement of the rotor blades in a turbo machine relative to the rotor disk comprises an annular extension or hook formed on each dovetail post on the web of the rotor disk, an impeller or blade retainer formed with a flange which is carried against the web and dovetail posts and a retaining ring interposed between the hooks of the dovetail posts and the flange of the impeller. The retaining ring secures the impeller in a fixed axial position relative to the dovetail posts and rotor disk, and is positioned to engage the rotor blades carried in the axial slots between adjacent dovetail posts to prevent their movement in a forward axial direction.

Boltless rotor blade retainer

Growing community of inventors

Cincinnati, OH, United States of America

Dennis Paul Dry