Ronald S Bunker

US Patent:

6350102, Feb 26, 2002

Filed:

Jul 19, 2000

Appl. No.:

09/575704

Inventors:

Jeremy Clyde Bailey - Middle Grove NY
Ronald Scott Bunker - Niskayuna NY

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 520

US Classification:

4151735

Abstract:

A turbine assembly includes a plurality of rotor blades comprising a root portion, an airfoil having a pressure sidewall and a suction sidewall, and a top portion having a cap. An outer shroud is concentrically disposed about said rotor blades, said shroud in combination with said tip portions defining a clearance gap. At least one circumferential shroud leakage discourager is disposed within the shroud. The leakage discourager(s) increase the flow resistance and thus reduce the flow of hot gas flow leakage for a given pressure differential across the clearance gap to improve overall turbine efficiency.

US Patent:

6427327, Aug 6, 2002

Filed:

Nov 29, 2000

Appl. No.:

09/726004

Inventors:

Ronald S. Bunker - Niskayuna NY

Assignee:

General Electric Company - Schenectady NY

International Classification:

B23P 1500

US Classification:

298891, 29889721

Abstract:

The cooling scheme of a gas turbine engine component is modified to improve local cooling without redesigning the investment casting. The modification includes forming at least one channel in the component such that the channel is in fluid communication with a cooling medium source associated with the component. The channel is then partially filled with a removable material, and the removable material is covered with a patch material so as to completely fill the channel. Lastly, the removable material is removed from the channel so as to create an internal cooling passage in the component that is in fluid communication with the cooling medium source.

US Patent:

6494678, Dec 17, 2002

Filed:

May 31, 2001

Appl. No.:

09/681744

Inventors:

Ronald Scott Bunker - Niskayuna NY

Assignee:

General Electric Company - Niskayuna NY

International Classification:

F01D 518

US Classification:

416 97R, 415115

Abstract:

A turbine assembly having at least one rotor blade comprises an airfoil having a pressure sidewall, a suction sidewall and a tip portion having a tip cap. A tip is disposed on the tip cap. A plurality of blade tip cooling holes are positioned within the airfoil near the tip portion. Cooling grooves are disposed within the airfoil to connect the blade tip cooling holes with the top portion of the tip to transition cooling flow from the cooling holes to the tip portion.

US Patent:

6504274, Jan 7, 2003

Filed:

Jan 4, 2001

Appl. No.:

09/754701

Inventors:

Ronald Scott Bunker - Niskayuna NY
Todd Garrett Wetzel - Niskayuna NY
Emil Donald Jarczynski - Scotia NY

Assignee:

General Electric Company - Schenectady NY

International Classification:

H02K 900

US Classification:

310 64, 310 52

Abstract:

A stator core assembly comprising adjacent packages of stacked lamination sheets that are separated by a plurality of radially extending spacer blocks, and each adjacent pair of spacer blocks define in cooperation with adjacent axially spaced laminations, a plurality of radial cooling ducts, each duct having a least one lamination surface having plurality of concavities.

US Patent:

6506022, Jan 14, 2003

Filed:

Apr 27, 2001

Appl. No.:

09/681553

Inventors:

Ronald Scott Bunker - Niskayuna NY

Assignee:

General Electric Company - Niskayuna NY

International Classification:

F01D 518

US Classification:

416 97R, 416191

Abstract:

A turbine blade having a cooled shroud comprises a blade attachment portion and a radially extended turbine airfoil integral with the blade attachment portion. The turbine airfoil has a plurality of cooling passages. A tip shroud is affixed to a top portion of the airfoil, the tip shroud having a plurality of circumferential cooling channels disposed substantially parallel to the rotation of the airfoil. Each circumferential cooling channel is in communication with a respective cooling passage and at least one exit port is in communication with at least one of the circumferential cooling channels.

US Patent:

6644921, Nov 11, 2003

Filed:

Nov 8, 2001

Appl. No.:

10/010549

Inventors:

Ronald Scott Bunker - Niskayuna NY
Bin Wei - Mechanicville NY

Assignee:

General Electric Company - Niskayuna NY

International Classification:

F01D 518

US Classification:

416 97R

Abstract:

A turbine portion, for example a turbine blade, for exposure in a hot fluid flow includes at least one internal cooling passage disposed therein. A cooling fluid is introduced within the cooling passage(s) to maintain the bulk temperature of the turbine portion at some acceptable temperature level. A plurality of concavities are disposed on the interior surface of the cooling passage. In one embodiment, the concavities are formed on the interior surface of cooling passage in an array pattern such that a spiral bulk fluid motion is obtained, similar to that which would be formed by a helical rib, but without the rib. The concavity surface pattern serves to enhance heat transfer to the same degree as the conventional rib rougheners, but with significantly less pressure loss due to friction. The spiral motion of the bulk cooling fluid also serves to recirculate central coolant to the heat transfer surface, thereby making the heat exchange process more effective than that for turbulated surfaces.

US Patent:

6681578, Jan 27, 2004

Filed:

Nov 22, 2002

Appl. No.:

10/065814

Inventors:

Ronald Scott Bunker - Niskayuna NY

Assignee:

General Electric Company - Schenectady NY

International Classification:

F02C 100

US Classification:

60772, 60759

Abstract:

A combustor liner for a gas turbine includes a substantially cylindrical body having a plurality of raised circular ribs arranged in an array on an outside surface of the combustor liner, each rib defining an enclosed are on the outside surface of the liner, forming a dimple or bowl that is sufficient to form vortices for fluid mixing in order to bring about heat transfer enhancement by both turbulated effect and dimpled effect.

US Patent:

6695582, Feb 24, 2004

Filed:

Jun 6, 2002

Appl. No.:

10/162739

Inventors:

Ronald Scott Bunker - Niskayuna NY
Frederic Joseph Klug - Schenectady NY
Shyh-Chin Huang - Latham NY

Assignee:

General Electric Company - Niskayuna NY

International Classification:

F01D 518

US Classification:

416 96R, 416232, 416236 R

Abstract:

A turbine blade comprises an external pressure side plate comprising a plurality of external pressure ribs, an internal pressure side plate comprising a plurality of internal pressure ribs, and a plurality of pressure flow redirection areas. The external pressure side plate is disposed over the internal pressure side plate to form a pressure side double wall. The external pressure ribs are disposed at a first angle with respect to a blade span reference line and the internal pressure ribs are disposed at a second angle with respect to the blade span reference line to form the pressure flow redirection areas. The pressure side double wall is configured to pass a coolant through the pressure side double wall. A fabrication method aligns the external pressure side plate and the internal pressure side plate to form the pressure flow redirection areas between the external pressure side plate and the internal pressure side plate.