Henry S Mutch

US Patent:

49984098, Mar 12, 1991

Filed:

Sep 25, 1989

Appl. No.:

7/411992

Inventors:

Henry Mutch - Chula Vista CA

Assignee:

Rohr Industries, Inc. - Chula Vista CA

International Classification:

F02K 172

US Classification:

602262

Abstract:

A thrust ring assembly for use in a thrust reverser system for a gas turbine engine. The ring assembly is useful in a turbine engine having a core engine surrounded by an engine casing and nacelle, with a fan at the inlet directing air flow into the bypass duct between core engine and nacelle. The thrust reverser basically comprises at least one opening through the engine casing and nacelle, a turning vane cascade in the opening, a cover movable by an actuator between positions covering and uncovering the opening and at least one blocker door movable between a position allowing flow through the bypass duct and a position diverting flow to the turning vane cascade. The actuator and cascade are severely aerodynamically loaded during thrust reversal. The improved thrust ring assembly carriers those loads and transfers them to the engine casing. The forward ends of the cascade and actuator are secured to a bulkhead ring which is secured to the base of a frustoconical ring.

US Patent:

51016214, Apr 7, 1992

Filed:

Sep 25, 1989

Appl. No.:

7/411991

Inventors:

Henry Mutch - Chula Vista CA

Assignee:

Rohr Industries, Inc. - Chula Vista CA

International Classification:

F02K 302
B32B 312

US Classification:

602261

Abstract:

An engine shroud with integral honeycomb panel corners for use in the thrust reverser region of ducted fan gas turbine engines. The integral shroud is useful in a turbine engine having a core engine surrounded by an engine casing and nacelle, with a fan at the inlet directing air flow into the bypass duct between core engine and engine nacelle. The shroud basically consists of right and left ducts each having an approximately semicircular cross-section with radial flanges extending from the duct edges. The flanges permit the halves to be fastened together to produce a tubular shroud adapted to surround a gas turbine engine and form the inner wall of a bypass duct. The disclosed shroud eliminates the prior complex corner fittings connecting the semicircular center portion of the shroud to the extending flanges and provides simple, integral corners.

US Patent:

50542818, Oct 8, 1991

Filed:

Sep 25, 1989

Appl. No.:

7/411643

Inventors:

Henry Mutch - Chula Vista CA

Assignee:

Rohr Industries, Inc. - Chula Vista CA

International Classification:

F02C 712

US Classification:

60 3983

Abstract:

A system for selectively venting cool bypass duct air into selected locations between a gas turbine engine and the engine shroud. The venting system is useful in a turbine engine having a core engine surrounded by an engine casing and nacelle, with a fan at the inlet directing air flow into the bypass duct between core engine and engine casing. The venting system basically comprises tubes inserted in holes in the engine shroud which separates the bypass duct from the engine compartment. Often sensors, electronic components or the like are advantageously located in the engine compartment. However, elevated temperatures in the engine compartment often damages or degrades those components. The vent tubes are positioned so as to direct cool air onto those components. A large number of vents may be provided in the shroud as manufactured, each plugged at manufacture, with only those opened which are needed for a specific engine with specifically located heat sensitive components.

US Patent:

40058360, Feb 1, 1977

Filed:

Dec 22, 1975

Appl. No.:

5/643493

Inventors:

Henry Mutch - Chula Vista CA

Assignee:

Rohr Industries, Inc. - Chula Vista CA

International Classification:

B64C 1504
B63H 1110

US Classification:

244110B

Abstract:

A thrust reversal system for an aircraft jet engine comprising a pair of thrust reverser doors constructed of a thin flexible material movable between a stowed and a deployed position and mechanism for moving same.