Edward C Mcdonough

US Patent:

41696921, Oct 2, 1979

Filed:

Dec 13, 1974

Appl. No.:

5/532701

Inventors:

Edward C. McDonough - Cincinnati OH
Eugene N. Tuley - Hamilton OH

Assignee:

General Electric Company - Cincinnati OH

International Classification:

F01D 518

US Classification:

415115

Abstract:

A cantilevered turbine vane of the variable area variety is provided with unique retaining means to prevent relative movement between the vane and a fixed turbine housing through which the vane trunnion passes. Vernier adjusting means are provided to maintain a predetermined radial clearance between the vane and the fixed turbine housing, thereby eliminating binding between the two structures.

US Patent:

40711943, Jan 31, 1978

Filed:

Oct 28, 1976

Appl. No.:

5/736299

Inventors:

Terry T. Eckert - Fairfield OH
Edward C. McDonough - Lawrenceburg IN

Assignee:

The United States of America as represented by the Secretary of the Navy - Washington DC

International Classification:

B64D 3308

US Classification:

2391273

Abstract:

A cooling arrangement for a gas turbine exhaust nozzle is provided which ludes a plurality of heat shield panels slidably positioned on tracks mounted on the nozzle casing. The panels are spaced apart to permit thermal expansion and include impingement baffles which are attached thereto intermediate the panels and the casing. Holes in the impingement baffles direct cooling air against the interior surface of the panels. The cooling air is directed by suitable means such as slots or film holes to form a film of cooling air along the surface of the panels exposed to hot gases.

US Patent:

41636295, Aug 7, 1979

Filed:

Dec 23, 1977

Appl. No.:

5/864049

Inventors:

Edward C. McDonough - Lawrenceburg IN
Eugene N. Tuley - Hamilton OH

Assignee:

The United States of America as represented by the Secretary of the Air
Force - Washington DC

International Classification:

F01D 2512
F02C 718

US Classification:

415115

Abstract:

A variable area turbine vane, for use in high temperature aircraft gas turbines, having a load carrying spar with a heat shield member surrounding the load carrying member. The heat shield member is positioned in grooves which permit spanwise and cordwise expansion of the heat shield member. Cooling air enters the hollow load bearing member and passes through holes in the load bearing member and heat shield member.