Bhanu Reddy

US Patent:

6595748, Jul 22, 2003

Filed:

Aug 2, 2001

Appl. No.:

09/921432

Inventors:

David Allen Flodman - Rowley MA
Bhanu Mahasamudram Reddy - Boxford MA
Mark Douglas Gledhill - Hamilton MA

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 518

US Classification:

416 97R, 415115

Abstract:

A turbine blade includes an airfoil having a leading edge flow chamber disposed behind a leading edge in front of a pair of side channels. The leading edge channel receives coolant from the pressure side channel in isolation from the suction side channel.

US Patent:

8281604, Oct 9, 2012

Filed:

Dec 17, 2007

Appl. No.:

11/957539

Inventors:

Mark Broomer - Boston MA, US
Victor Hugo Silva Correia - Milton Mills MA, US
Robert Francis Manning - Newburyport MA, US
Stephen Kin-Keung Tung - Andover MA, US
Bhanu Mahasamudram Reddy - Boxford MA, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F02C 7/12

US Classification:

60806, 415115

Abstract:

A turbine nozzle includes a row of vanes extending radially in span between inner and outer bands. The vanes include opposite pressure and suction sidewalls and opposite leading and trailing edges. Each vane includes an inner pattern of inner cooling holes and an outer pattern of outer cooling holes distributed along the leading edge. The inner and outer holes diverge toward the corresponding inner and outer bands to preferentially discharge cooling air.

US Patent:

61683817, Jan 2, 2001

Filed:

Jun 29, 1999

Appl. No.:

9/342822

Inventors:

Bhanu M. Reddy - Boxford MA

Assignee:

General Electric Company - Cincinnati OH

International Classification:

F01D 518

US Classification:

416 97R

Abstract:

A turbine blade includes an airfoil having a leading edge flow chamber disposed behind a leading edge in flow communication with an isolation flow channel disposed therebehind. The isolation channel is bounded on opposite sides by a pair of side flow channels.

US Patent:

61649139, Dec 26, 2000

Filed:

Jul 26, 1999

Appl. No.:

9/360923

Inventors:

Bhanu M. Reddy - Boxford MA

Assignee:

General Electric Company - Cincinnati OH

International Classification:

F01D 508

US Classification:

416 97R

Abstract:

A turbine airfoil includes first and second sidewalls joined together at leading and trailing edges, and extending longitudinally from root to tip. An internal cooling circuit is disposed between the sidewalls for channeling a coolant therein. A column of longitudinally spaced apart ejection slots extend through the first sidewall along the trailing edge, and are disposed in flow communication with the cooling circuit for discharging the coolant toward the trailing edge. Some of the slots are disposed between a pitchline and the tip and are inclined at different ejection angles longitudinally outwardly from the pitchline. And, some of the slots are disposed between the pitchline and root and extend at least parallel with the pitchline without longitudinally inward inclination.

US Patent:

20170226869, Aug 10, 2017

Filed:

Feb 8, 2016

Appl. No.:

15/018155

Inventors:

- Schenectady NY, US
Bhanu Mahasamudram Reddy - Boxford MA, US
Gaoqiu Zhu - Andover MA, US
Michael Jong Lee - Peabody MA, US

International Classification:

F01D 5/18
F01D 25/12
F01D 9/04

Abstract:

An apparatus and method of cooling an airfoil for a gas turbine engine includes a tip for the radially outer end of the airfoil with internal ribs defining cooling circuits within an interior of the airfoil. The ribs can be full-length, extending between a root and tip of the airfoil. A gap can be formed in the full-length ribs near the tip to form a thermal stress reduction structure for the full-length rib.