William G Monsarrat

US Patent:

44313730, Feb 14, 1984

Filed:

May 16, 1980

Appl. No.:

6/150490

Inventors:

William G. Monsarrat - South Windsor CT

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F04D 2954

US Classification:

415189

Abstract:

A nonrotating flow directing assembly 14 for a gas turbine engine is disclosed. The flow directing assembly is formed of a circumferentially segmented inner case 24 supported by an annular sleeve 22. The inner case 24 is formed of a plurality of arcuate segments 26 extending axially continuously through the engine. A method of assembling the circumferentially continuous annular sleeve about an axially continuous rotor is also disclosed. In an alternate embodiment the inner case 124 is formed of several pluralities of arcuate segments 126.

US Patent:

49341405, Jun 19, 1990

Filed:

May 13, 1988

Appl. No.:

7/193473

Inventors:

William T. Dennison - Vernon CT
William G. Monsarrat - Baltic CT
Robert F. Brodell - Marlborough CT

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F02K 304

US Classification:

602261

Abstract:

A gas turbine fan engine with improved maintainability features is disclosed. Forward and rearward sections of the core of the engine are joined one to the other, and each are independently separable from the pylon on which the engine is mounted without the necessity of removing the other from the airplane.

US Patent:

42682215, May 19, 1981

Filed:

Mar 28, 1979

Appl. No.:

6/024636

Inventors:

William G. Monsarrat - South Windsor CT
William F. Neal - South Windsor CT

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F02C 716

US Classification:

415116

Abstract:

A compressor structure for a gas turbine engine capable of enhanced active clearance control within the compressor is disclosed. Various construction details which enable the discharge of cooling air against the compressor case and which minimize thermal distortion of the case are developed. The concepts are applied to a longitudinally split compressor case and include an external bleed manifold of circular cross section which extends across the longitudinal split in the case. Cooling air is dischargeable beneath the manifold to cool the case structure. Heat shields are provided in access ports to the manifold to inhibit heat transfer to the compressor case at the local regions of the ports.

US Patent:

44127820, Nov 1, 1983

Filed:

Mar 28, 1979

Appl. No.:

6/024635

Inventors:

William G. Monsarrat - South Windsor CT

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F01D 508
F01D 518
F01D 1100
F01D 2508

US Classification:

415175

Abstract:

A compressor case structure capable of enhanced active clearance control within the structure is disclosed. Various construction details which enable the discharge of cooling air against the case and which minimize thermal distortion of the case are developed. The concepts are applied to a longitudinally split compressor case and include an external bleed manifold or circular cross section which extends across the longitudinal split in the case. Cooling air is dischargeable beneath the manifold to cool the case structure.

US Patent:

47442140, May 17, 1988

Filed:

Jun 29, 1987

Appl. No.:

7/067339

Inventors:

William G. Monsarrat - Willimantic CT
Robert F. Brodell - Marlborough CT

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F02K 302

US Classification:

602261

Abstract:

The low pressure compressor and fan together with the intermediate case are removable as a unit from the core engine by removal of the nose cone and a stub shaft at the front of the low pressure turbine shaft and at the ID of the fan hub (50) to provide access to attachment bolts at the inner portion of the intermediate case which holds the bearing for the high pressure rotor in position within the intermediate case after assembly of the engine.