Bhanu M 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:

7431561, Oct 7, 2008

Filed:

Feb 16, 2006

Appl. No.:

11/356388

Inventors:

Tyler F. Hooper - Amesbury MA, US
Bhanu Reddy - Boxford MA, US
Gaoqiu Zhu - Billerica MA, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 5/18

US Classification:

416 96R, 416 97 R

Abstract:

Methods and apparatus for cooling gas turbine rotor blades is provided. The blade includes an airfoil having an internal three pass serpentine cooling circuit having radially extending first, second, and third serpentine cooling cavities partially separated by, in axially aft succession, a first radially extending internal rib and a second radially extending internal rib. The serpentine cooling circuit includes a first inlet in flow communication with the first cavity and a second inlet in flow communication with at least one of the second and third cavities wherein the first and second inlets are formed during casting of the airfoil.

US Patent:

7431562, Oct 7, 2008

Filed:

Dec 21, 2005

Appl. No.:

11/314756

Inventors:

Tyler F. Hooper - Amesbury MA, US
Bhanu Reddy - Boxford MA, US
Gaoqiu Zhu - Billerica MA, US
Robert F. Manning - Newburyport MA, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 5/08

US Classification:

416 97R

Abstract:

Methods and apparatus for cooling gas turbine rotor blades is provided. The rotor blades include an airfoil having a pressure sidewall and a second suction sidewall connected together at a leading edge and a trailing edge, such that an internal three pass serpentine cooling circuit is formed therebetween. The cooling circuit includes radially extending first, second, and third serpentine cooling cavities partially separated by, in axially aft succession, a first radially extending internal rib and a second internal rib. The second rib includes a radially inner first portion and a radially outer portion wherein the radially outer portion is angled obliquely with respect to the first portion.

US Patent:

7857587, Dec 28, 2010

Filed:

Nov 30, 2006

Appl. No.:

11/606731

Inventors:

Victor Hugo Silva Correia - Milton Mills NH, US
Robert Francis Manning - Newburyport MA, US
Bhanu Mahasamudram Reddy - Boxford MA, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 5/18
B64C 11/24

US Classification:

416 92, 416 97 R, 416228, 416235

Abstract:

A turbine blade with improved tip cooling includes an airfoil having a tip cap and a tip wall extending outwardly from the tip cap. A recessed portion of the tip wall forms a tip shelf. At least one tip shelf hole extends through the tip shelf in flow communication with an internal airfoil cooling circuit. At least one tip wall opening extends through the recessed portion of the tip wall radially outward of the tip shelf in flow communication with the internal cooling circuit. The recessed tip wall portion may be tapered from a wider base to a minimum thickness. In a cooling method, cooling air channeled through the tip wall openings joins and mixes with a stream of hot combustion gases downstream of where cooling air channeled through the tip shelf openings joins and mixes with the stream of hot gasses to enhance convection cooling of the blade tip. A system for cooling a blade includes at least one tip shelf hole and at least one tip wall opening for channeling cooling air from an internal cooling circuit toward a stream of hot combustion gases for improved cooling of at least the blade tip.

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:

8591189, Nov 26, 2013

Filed:

Nov 20, 2006

Appl. No.:

11/602137

Inventors:

Victor Hugo Silva Correia - Milton Mills NH, US
Robert Francis Manning - Newburyport MA, US
Bhanu Mahasamudram Reddy - Boxford MA, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 5/18

US Classification:

416 96R, 416 97 R

Abstract:

A turbine blade includes forward and aft serpentine cooling circuits terminating in corresponding forward and aft impingement channels. Each serpentine circuit has two metered inlets for distributing primary inlet flow to the first passes thereof and supplemental inlet flow to the last passes thereof.

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.