Andrew D Kemp

US Patent:

6550254, Apr 22, 2003

Filed:

Aug 17, 2001

Appl. No.:

09/932585

Inventors:

Robert Proctor - West Chester OH
Julius John Montgomery - Mason OH
Michael Jay Epstein - Mason OH
Roger Owen Barbe - Montgomery OH
Hai Buu Sam - Hamilton OH
James Bernar Ogzewalla - Maysville KY
Andrew David Kemp - Loveland OH
Bryan Keith Doloresco - Cincinnati OH

Assignee:

General Electric Company - Schenectady NY

International Classification:

F02C 608

US Classification:

60785, 415144

Abstract:

A gas turbine engine includes a compressor including a casing and a stator assembly. The casing extends around the stator assembly, the stator assembly including a plurality of stator vanes, and a plurality of bleed scoops. Adjacent stator vanes define a static high-pressure region, the bleed scoops formed at least partially within the high pressure region.

US Patent:

51545772, Oct 13, 1992

Filed:

Jan 17, 1991

Appl. No.:

7/642739

Inventors:

Iain R. Kellock - Hamilton OH
Andrew D. Kemp - Mason OH

Assignee:

General Electric Company - Cincinnati OH

International Classification:

F01D 520

US Classification:

4151701

Abstract:

A three-piece seal assembly is disclosed for sealing cooling air leakage between circumferentially spaced-apart flowpath segments in gas turbine engines. First and second seals are disposed in oppositely facing slots on adjacent flowpath segments, and extend between adjacent flowpath segments to restrict cooling flow between the segments. A third seal member having first and second leg portions in abutting engagement with the first and second seals restricts leakage flow between the gap between the first and second seals.

US Patent:

60957506, Aug 1, 2000

Filed:

Dec 21, 1998

Appl. No.:

9/217660

Inventors:

Steven A. Ross - Cincinnati OH
Robert J. Albers - Park Hills KY
Edward P. Brill - West Chester OH
Andrew D. Kemp - Loveland OH
Larry W. Plemmons - Hamilton OH

Assignee:

General Electric Company - Cincinnati OH

International Classification:

F01D 904

US Classification:

415189

Abstract:

A turbine nozzle assembly includes a plurality of nozzle segments and a nozzle support for supporting the nozzle segments. Each nozzle segment includes an outer band, an inner band and at least two vanes disposed between the outer and inner bands. A retention flange extends radially inwardly from the inner band and has a first hole formed therein. The nozzle support includes a recess formed therein and a mounting flange extending therefrom. The mounting flange is disposed in contact with the retention flange and has a second hole formed therein. A pin is disposed in the first and second holes to position the flanges with respect to one another. A pin retainer is disposed in the recess and has a holding flange for retaining the pin in place. The nozzle support includes a substantially conical portion and an air seal integrally formed thereto.

US Patent:

20160201565, Jul 14, 2016

Filed:

Oct 30, 2015

Appl. No.:

14/928077

Inventors:

- Schenectady NY, US
Arjan Johannes HEGEMAN - Cincinnati OH, US
Andrew David KEMP - Maineville OH, US
John Michael PYLES - West Chester OH, US

International Classification:

F02C 7/25

Abstract:

A method and system for a compartment baffle system are provided. The compartment baffle system includes a first baffle portion extending along an axial length of a casing, the first baffle portion extending radially outwardly from an outer surface of the casing and a second baffle portion extending at least partially radially outwardly from the first baffle portion. The second baffle portion further includes a radially inner edge supported by the first baffle portion and a radially outer edge extending proximate an inner surface of a radially outer cowl. The compartment baffle system also includes a gap extending between the radially outer edge and the inner surface.