Dennis P Dry

US Patent:

48909815, Jan 2, 1990

Filed:

Dec 30, 1988

Appl. No.:

7/292084

Inventors:

Robert J. Corsmeier - Cincinnati OH
Ronald E. Schlechtweg - Loveland OH
Richard W. Albrecht - Fairfield OH
Dennis P. Dry - Cincinnati OH

Assignee:

General Electric Company - Cincinnati OH

International Classification:

F01D 532

US Classification:

416220R

Abstract:

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.

US Patent:

58514090, Dec 22, 1998

Filed:

Dec 24, 1996

Appl. No.:

8/772959

Inventors:

Jon C. Schaeffer - Milford OH
Jeffrey A. Conner - Hamilton OH
Dennis P. Dry - Cincinnati OH
Gregory J. Anselmi - Fairfield OH
David C. Zigan - Episy, FR

Assignee:

General Electric Company - Cincinnati OH

International Classification:

C23F 400

US Classification:

216 2

Abstract:

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.

US Patent:

51833891, Feb 2, 1993

Filed:

Jan 30, 1992

Appl. No.:

7/828278

Inventors:

Alan R. Gilchrist - Fairfield OH
Edward M. Duran - Cincinnati OH
Dennis P. Dry - Cincinnati OH
Robert R. Berry - Portville NY

Assignee:

General Electric Company - Cincinnati OH

International Classification:

F01D 530

US Classification:

416193A

Abstract:

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.

US Patent:

20220333491, Oct 20, 2022

Filed:

Apr 16, 2021

Appl. No.:

17/232721

Inventors:

- Schenectady NY, US
Dennis Paul Dry - Cincinnati OH, US
Todd William Bachmann - Edgewood KY, US

International Classification:

F01D 5/28
F01D 5/30

Abstract:

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.

US Patent:

20190338676, Nov 7, 2019

Filed:

Jun 27, 2019

Appl. No.:

16/454975

Inventors:

- Schenectady NY, US
Mark Eugene Noe - West Chester OH, US
Dennis Paul Dry - Cincinnati OH, US
Brandon ALlanson Reynolds - Cincinnati OH, US

International Classification:

F01D 25/24
F23R 3/00
F23R 3/60
F23R 3/50

Abstract:

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.

US Patent:

20190063250, Feb 28, 2019

Filed:

Aug 30, 2017

Appl. No.:

15/690307

Inventors:

- Schenectady NY, US
Dennis Paul Dry - Cincinnati OH, US
Christopher Edward Wolfe - Niskayuna NY, US
Andres Jose Garcia-Crespo - Redondo Beach CA, US
Yun Zhu - Clifton Park NY, US

International Classification:

F01D 11/12
F01D 5/20
F01D 5/28
F01D 5/18

Abstract:

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.

US Patent:

20180355760, Dec 13, 2018

Filed:

Jun 12, 2017

Appl. No.:

15/620134

Inventors:

- Schenectady NY, US
Mark Eugene Noe - West Chester OH, US
Dennis Paul Dry - Cincinnati OH, US
Brandon ALlanson Reynolds - Cincinnati OH, US

International Classification:

F01D 25/24
F23R 3/60
F23R 3/00
F01D 25/28

Abstract:

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.

US Patent:

20180195403, Jul 12, 2018

Filed:

Jan 12, 2017

Appl. No.:

15/404608

Inventors:

- Schenectady NY, US
Dennis Paul Dry - Cincinnati OH, US
Megan Elizabeth Scheitlin - Cincinnati OH, US
Alexander Martin Sener - Cincinnati OH, US
Jason David Shapiro - Methuen MA, US

International Classification:

F01D 11/10
F01D 25/24
F02C 7/28
F04D 29/52
F04D 29/54
F02C 3/04
F04D 29/64

Abstract:

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.