David M Kercher

US Patent:

6478540, Nov 12, 2002

Filed:

Dec 19, 2000

Appl. No.:

09/739445

Inventors:

Nesim Abuaf - Lincoln City OR
Kevin Joseph Barb - Halfmoon NY
Sanjay Chopra - Greenville SC
David Max Kercher - Ipswich MA
Iain Robertson Kellock - Simpsonville SC
Dean Thomas Lenahan - Cincinnati OH
Sankar Nellian - Mauldin SC
John Howard Starkweather - Sharonville OH
Douglas Arthur Lupe - Ballston Lake NY

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 518

US Classification:

416 1, 416 97 R, 416193 A

Abstract:

A turbine bucket includes an airfoil extending from a platform, having high and low pressure sides; a wheel mounting portion; a hollow shank portion located radially between the platform and the wheel mounting portion, the platform having an under surface. An impingement cooling plate is located in the hollow shank portion, spaced from the under surface, and the impingement plate is formed with a plurality of impingement cooling holes therein.

US Patent:

56904738, Nov 25, 1997

Filed:

Aug 25, 1992

Appl. No.:

7/935066

Inventors:

David Max Kercher - Ipswich MA

Assignee:

General Electric Company - Cincinnati OH

International Classification:

F01D 518

US Classification:

416 97A

Abstract:

A gas turbine engine turbine blade and method of manufacture includes an airfoil having pressure and suction sides joined together at leading and trailing edges. The airfoil further includes a supply channel for receiving compressed air, and has an elongate recess disposed in at least one of the pressure and suction sides which is separated from the supply channel by a partition. The partition includes a plurality of spaced apart flow metering holes disposed in flow communication with the supply channel. A transpiration strip is fixedly joined to the airfoil in the recess and spaced from the partition to define a plenum for receiving the compressed air from the metering holes. The transpiration strip is pervious for channeling the compressed air from the plenum in a blanket of film cooling boundary layer air therefrom.

US Patent:

56953208, Dec 9, 1997

Filed:

Dec 17, 1991

Appl. No.:

7/809602

Inventors:

David Max Kercher - Ipswich MA

Assignee:

General Electric Company - Cincinnati OH

International Classification:

F01D 518

US Classification:

416 97R

Abstract:

A gas turbine blade includes an airfoil having first and second sides and an internal passage extending longitudinally therebetween for channeling air to cool the airfoil. A plurality of longitudinally spaced apart primary turbulator ribs extend into the internal passage from at least one of the first and second sides. An auxiliary turbulator rib is spaced between adjacent ones of the primary ribs. The auxiliary rib has a height which is less than the height of the primary ribs for augmenting convective heat transfer enhancement with reduced pressure loss, and, therefore, reduced cooling air requirements.

US Patent:

62870750, Sep 11, 2001

Filed:

Oct 22, 1997

Appl. No.:

8/955226

Inventors:

David M. Kercher - Ipswich MA

Assignee:

General Electric Company - Cincinnati OH

International Classification:

F01D 518

US Classification:

416 97R

Abstract:

A turbine airfoil includes a leading edge, a trailing edge, and a root and tip spaced apart along a span axis. First and second airfoil sides extend therebetween. A cooling circuit is disposed between the sides for channeling a cooling fluid. A plurality of diffusion fan holes are spaced apart along the span axis in the airfoil first side, with each fan hole increasing in flow area between an inlet at the cooling circuit and an outlet on the airfoil first side disposed coaxially about a centerline fan axis. The fan axis is inclined at an acute span angle, with the outlet being greater in span height than the inlet, and substantially equal in width for increasing coverage of the outlets and film cooling air therefrom along the span axis.

US Patent:

56953216, Dec 9, 1997

Filed:

Dec 17, 1991

Appl. No.:

7/809603

Inventors:

David Max Kercher - Ipswich MA

Assignee:

General Electric Company - Cincinnati OH

International Classification:

F01D 518

US Classification:

416 97R

Abstract:

A turbine blade includes an airfoil having opposite first and second sides and an internal passage extending longitudinally therebetween. A plurality of turbulator ribs extend from the first side into the passage and have substantially identical configurations including first and second ends having a span axis extending therebetween, first and second sides having a width therebetween, and a base and a tip having a height e measured therebetween. The passage includes a height H for defining a rib-to-passage height ratio e/H. Adjacent ribs are spaced apart at a longitudinal spacing S for defining a rib spacing-to-height ratio S/e. The rib configuration varies along the span axis between the rib first and second ends for correspondingly varying at least one of the ratios e/H and S/e to effect a varying convective heat transfer enhancement along the rib span axis for increasing enhancement and reducing cooling airflow.

US Patent:

62243365, May 1, 2001

Filed:

Jun 9, 1999

Appl. No.:

9/328470

Inventors:

David M. Kercher - Ipswich MA

Assignee:

General Electric Company - Cincinnati OH

International Classification:

F01D 518
F01D 520

US Classification:

416 97R

Abstract:

A turbine airfoil includes pressure and suction sidewalls extending between leading and trailing edges and from root to tip. The tip includes a floor bounding an internal cooling channel within the airfoil which channels cooling air. The airfoil tip includes a first rib adjacent the pressure sidewall, a second rib spaced therefrom to define a first slot, and a third rib adjacent the suction sidewall to define a second slot with the second rib. The tip floor includes feed holes extending between the cooling channel and the first slot for supplying cooling air therein for discharge over the second rib towards the third rib.

US Patent:

53562658, Oct 18, 1994

Filed:

Aug 25, 1992

Appl. No.:

7/935061

Inventors:

David M. Kercher - Ipswich MA

Assignee:

General Electric Company - Cincinnati OH

International Classification:

F01D 518

US Classification:

416 97R

Abstract:

A gas turbine engine turbine blade includes an airfoil having pressure and suction sides joined together at leading and trailing edges and extending from a root to a tip. The airfoil also includes a longitudinally extending flow channel for receiving compressed air, with the flow channel including a chordally extending, imperforate septum dividing the flow channel into first and second laterally spaced apart flow chambers. The blade further includes a supply manifold for receiving the compressed air at a single pressure which is disposed in flow communication with both the first and second chambers for channeling thereto respective first and second portions of the compressed air. The septum is used to reduce or eliminate radial velocity distortion, or blowoff of film cooling air from the suction side.