Edward C Rice

US Patent:

6347508, Feb 19, 2002

Filed:

Mar 22, 2000

Appl. No.:

09/532253

Inventors:

Michel Shawn Smallwood - Indianapolis IN
Edward Claude Rice - Indianapolis IN

Assignee:

Allison Advanced Development Company - Indianapolis IN

International Classification:

F02C 720

US Classification:

60 3931

Abstract:

The present invention contemplates an apparatus for supporting an annular combustor liner in a gas turbine engine. In one embodiment, the apparatus includes a plurality of radial lugs extending outwardly from an outer surface of the combustor liner and being spaced circumferentially and uniformly about a periphery of the combustor liner. A band is disposed about the outer surface of the combustor liner and coupled to the radial lugs. The radial lugs each include a radially extending slot having opposing circumferentially facing radial surfaces. The band includes a plurality of pins, each pin being disposed within a respective one of the slots. The pin is configured to bear against at least one of the radial surfaces to provide circumferential support to the combustor liner by substantially preventing relative circumferential movement between the combustor liner and the band. The pin is slidable between the radial surfaces to allow relative radial movement between the combustor liner and the band.

US Patent:

6351949, Mar 5, 2002

Filed:

Sep 3, 1999

Appl. No.:

09/390147

Inventors:

Edward Claude Rice - Indianapolis IN
Timothy Carl Roesler - Plainfield IN

Assignee:

Allison Advanced Development Company - Indianapolis IN
Rolls-Royce Corporation - Indianapolis IN

International Classification:

F02C 100

US Classification:

60752, 60759, 403316

Abstract:

An interchangeable combustor chute for directing airflow into a gas turbine engine combustor. In one aspect the combustor chute is secured to the combustor liner by mechanical fastener. The combustor chute is formed of a high temperature resistant material such as ceramics.

US Patent:

6364606, Apr 2, 2002

Filed:

Nov 8, 2000

Appl. No.:

09/708826

Inventors:

Edward C. Rice - Indianapolis IN
Jack D. Petty - Indianapolis IN

Assignee:

Allison Advanced Development Company - Indianapolis IN

International Classification:

F01D 900

US Classification:

415189, 4152131, 4152141

Abstract:

A high temperature capable flange is disclosed where the use of bolts is minimized or eliminated. The flange is intended for use in a gas turbine engine extending generally along a central axis. The loads between a hanger and an inner case, a hanger and a seal, or between all three are transmitted through pin arrangements that are substantially radially located. The hanger, inner case and seal all include generally ring shaped portions that are at least partially overlapping. The ring shaped portions of the components may have a variety of radially overlapping cavities for receiving the pins in different arrangements.

US Patent:

6401447, Jun 11, 2002

Filed:

Nov 8, 2000

Appl. No.:

09/708945

Inventors:

Edward C. Rice - Indianapolis IN
Spencer D. Pack - Middletown CT

Assignee:

Allison Advanced Development Company - Indianapolis IN

International Classification:

F02C 720

US Classification:

60 3931, 60 3932, 60751

Abstract:

A combustor apparatus for a gas turbine engine includes a combustor liner support having an annular dome panel and a plurality of load transfer members extending axially therefrom. The dome panel maintains inner and outer combustor liners in spaced relation to define a combustion chamber. The load transfer members extend into a diffuser flowpath defined by inner and outer flowpath structures which are interconnected by a plurality of struts. Each of the load transfer members surrounds at least a portion of a corresponding strut to shield the strut from fluid flowing through the diffuser flowpath.

US Patent:

6418727, Jul 16, 2002

Filed:

Mar 22, 2000

Appl. No.:

09/532636

Inventors:

Edward C. Rice - Indianapolis IN

Assignee:

Allison Advanced Development Company - Indianapolis ID

International Classification:

F02C 720

US Classification:

60799

Abstract:

The present invention contemplate a seal assembly for reducing the passage of fluid between a combustor liner and a turbine vane segment in a gas turbine engine. In one embodiment, the turbine vane segment has a lip portion defining a sealing surface. A seal element having first and second seal portion is coupled to the turbine vane segment by a support element. The support element urges the first seal portion into engagement with an aft edge of the combustor liner and positions the second seal portion adjacent the sealing surface of the turbine vane segment, while allowing relative movement between the second seal portion and the sealing surface in a direction substantially parallel to the sealing surface.

US Patent:

6422020, Jul 23, 2002

Filed:

Mar 13, 2000

Appl. No.:

09/523815

Inventors:

Edward C. Rice - Indianapolis IN

Assignee:

Allison Advanced Development Company - Indianapolis IN

International Classification:

F02C 7141

US Classification:

60730, 60736

Abstract:

A cast heat exchanger, having an inlet and an outlet and defining an internal passage therebetween, includes a wall structure disposed within the internal passage that defines a series of interconnected chambers through which a cooling medium flows in a serpentine path. The outer surface of the heat exchanger is covered with pin fins that transfer heat away from the hot working medium flowing over the pin fins and into the cooling medium within the chambers of the heat exchanger.

US Patent:

6564555, May 20, 2003

Filed:

May 24, 2001

Appl. No.:

09/864716

Inventors:

Edward C. Rice - Indianapolis IN
Brian P. King - Greenwood IN

Assignee:

Allison Advanced Development Company - Indianapolis IN

International Classification:

F02C 100

US Classification:

60746, 60740

Abstract:

The present invention contemplates an apparatus for forming a combustion mixture in a gas turbine engine. In one form, the apparatus includes a diffuser having at least two flowpath structures spaced apart to define a flowpath for directing fluid flow. At least one of the flowpath structures includes a flowpath surface and a plurality of edges disposed along a trailing end portion of the flowpath surface. The edges extend perpendicularly from the flowpath surface and are arranged generally parallel to the fluid flow to define a plurality of corners. A fluid vortex is generated as the fluid flow rolls over each of the corners. A spray ring is disposed along a trailing edge of one of the flowpath structures and is integrally attached to the diffuser. The spray ring includes a plurality of fuel delivery apertures adapted to spray fuel into respective ones of the fluid vortices to form the combustion mixture.

US Patent:

6513330, Feb 4, 2003

Filed:

Nov 8, 2000

Appl. No.:

09/708930

Inventors:

Edward C. Rice - Indianapolis IN
Kenneth W. Froemming - Carmel IN

Assignee:

Allison Advanced Development Company - Indianapolis IN

International Classification:

F02C 100

US Classification:

60751

Abstract:

An annular diffuser for a gas turbine engine includes inner and outer walls spaced apart to define a diffuser flow path, and a support member coupling the inner wall to the outer wall while allowing independent radial displacement therebetween. The support member includes a first end portion rigidly connected to the inner wall, and a second end portion extending outside of the diffuser flowpath and coupled to the outer wall by a radially extending pin. An aerodynamically-shaped shroud member surrounds the support member to thermally isolate the support member from the diffuser flowpath, thereby shielding the support member from transient thermal loads. The shroud member is pinned to the support member at a single axial location. A combustor dome panel is attached to the downstream end portion of the shroud member and is adapted to independently support inner and outer combustor liners in spaced relation to define a combustion chamber therebetween.