Rohr, Inc.

Other

United Technologies Corporation

Aleksandar Ratajac

Michael R Aten

Steven H Zysman

Jihad I Ramlaoui

Jeffrey W Moe

Jean C Langlois

Gary Dubie

John E Van Doren

Joseph Christopher Zecca

Daniel Kroeger

Colin Roy Terrey

Kristopher B Shaner

Bahram B Graily

Rosa Gonzalez

Bobby Ratayats

Bahram Graily

An assembly for an aircraft propulsion system includes a nacelle inlet structure. The nacelle inlet structure includes an inlet lip, an inner barrel, an outer barrel, a bulkhead and a plurality of structure segments. Each of the structure segments includes an exterior skin, an inner mount flange, an outer mount flange and an electric heater configured to heat the exterior skin. The exterior skin forms at least a respective circumferential section of the inlet lip. The inner mount flange is connected to and projects radially outward away from the exterior skin. An inner fastener extends axially through the inner mount flange and couples the inner mount flange to the inner barrel. The outer mount flange is connected to and projects radially inward away from the exterior skin. An outer fastener extends axially through the outer mount flange and couples the outer mount flange to the bulkhead.

Segmented nacelle inlet lip with electric anti-icing system

An assembly is provided for an aircraft propulsion system. This assembly includes a nacelle inlet structure which extends axially along and circumferentially around a centerline. The nacelle inlet structure includes an inlet lip, an inner barrel, an outer barrel and a plurality of structure segments. The inlet lip forms a leading edge of the nacelle inlet structure. The inner barrel projects axially aft away from the inlet lip. The outer barrel projects axially aft away from the inlet lip. The outer barrel is radially outboard of and axially overlaps the inner barrel. Each of the structure segments includes an exterior skin, a mount and an electric heater configured to heat the exterior skin. The exterior skin forms a respective circumferential section of the inlet lip and a respective circumferential section of the outer barrel. The mount is bonded to the exterior skin and mechanically attached to the inner barrel.

A wall structure is provided for an aircraft. This wall structure includes a first wall section, a second wall section and a fastener system fastening the second wall section to the first wall section. The second wall section includes an aperture extending axially along an axis through the second wall section. The second wall section is axially spaced from the first wall section. The fastener system includes a mount and a retainer. The mount is connected to the first wall section. The mount includes a post that projects axially into the aperture. The retainer includes a head and a spring clip connected to the head. The head axially engages the second wall section. The spring clip is disposed in the aperture and is mated with the post.

Push-on retainer(s) for an aircraft wall structure

A fluid conduit assembly is provided that includes a first conduit coupler, a second conduit coupler and a lock. The second conduit coupler is mated with the first conduit coupler at a threaded interface. The lock is configured to rotationally fix the first conduit coupler with the second conduit coupler. The lock includes a flange, a clip and a fastener. The flange is arranged with the first conduit coupler. The flange is configured with a plurality of flange apertures arranged circumferentially about an axis of the first conduit coupler. The clip is arranged with the second conduit coupler. The clip is configured with a clip aperture. The fastener is mated with the clip aperture and any one of the plurality of flange apertures.

Conduit fluid coupling with anti-rotation lock

An anti-icing system is disclosed. In various embodiments, the anti-icing system includes an inner duct having a first end configured to deliver heated gas to a plenum and a second end spaced from the first end; an outer duct circumferentially encompassing at least a portion of the inner duct; and a seal system disposed proximate the second end, the seal system including a first annular seal having a radially inner end positioned proximate a flange disposed on the inner duct.

Anti-ice double walled duct system

An assembly is provided for an aircraft propulsion system. This assembly includes a first component, a second component and a tubular fire seal. The first component includes a first passage. The second component includes a second passage. The tubular fire seal seals a gap between the first component and the second component. The tubular fire seal includes an outer shroud. At least a portion of the outer shroud has a wavy sectional geometry. The first passage is fluidly coupled with the second passage through an inner bore of the tubular fire seal.

Tubular seal with wavy shroud for an aircraft propulsion system

An aircraft cowl arrangement may comprise a first half, and a second half rotatable between an open position and a closed position, a first seal coupled to the first half, a second seal coupled to the second half, and a latch arrangement for preventing relative movement between the first half and the second half. The latch arrangement may comprise a tie rod comprising a first end coupled to the first half, a second end, and a frame having an opening for receiving the second end of the tie rod, a latch handle rotatably mounted to the frame, and a hook operably coupled to the latch handle, wherein the latch handle is configured to move between a first position wherein the hook is engaged with the second end of the tie rod and a second position wherein the hook is disengaged from the second end of the tie rod.

Fan cowl latch concept for fuselage mounted power plant

A portable exercise device for exercising the muscles of the upper body and thighs. The device comprises a pair of elongate members having a body engaging element for receiving the thighs of the user to hold the device in a stable, fixed position, a spring portion that joins the elongate members in a generally parallel configuration, and optionally a pair of handgrips at the ends of the elongate members. Methods of using the device of the invention are also provided.

Exercise device

Methods and fire sealing systems for a panel of a gas turbine engine are provided. The fire sealing systems include a thermal blanket mounted on the panel, the thermal blanket having a close-out and defining a seal landing at a periphery edge of the panel, a seal retainer mounted to the panel along the seal landing, and a fire seal securely retained within the seal retainer, wherein at least one of the seal retainer or the fire seal comprises an extension portion and a blanket engaging portion such that a close-out volume formed between the thermal blanket and the fire seal above the close-out of the thermal blanket is enclosed.

Close-out enclosure for panel of a gas turbine engine

An assembly is provided for an aircraft propulsion system. The assembly includes a first component, a second component and a seal assembly configured to seal a gap between the first and the second components. The seal assembly includes a metal spring seal element and an elastomeric seal element. The metal spring seal element is mounted to the first component. The metal spring seal element is sealingly engaged with the second component. The elastomeric seal element is mounted to the metal spring seal element. The elastomeric seal element is sealingly engaged with the second component.

Aircraft propulsion system seal assembly with spring seal element and compliant seal element

A hybrid inner fixed structure is disclosed. The inner fixed structure may have an inner fixed structure panel having an inner fixed structure panel surface and an inset panel having an inset panel surface disposed in at least partial contact with a first portion of the inner fixed structure panel surface. In this manner, a hybrid inner fixed structure may be designed to be both lightweight and heat tolerant.

Hybrid IFS with metallic aft section

A mounting system for a fire detection system for a turbofan engine propulsion system is provided to mount fire detection sensors on the inner fixed structure (IFS) of the nacelle. The mounting system mounts to an inner, engine facing surface of the IFS. Two IFS halves cooperate to form a substantially enclosed space around an engine core. The mounting system includes part of a fastening system mounted to the IFS, and an orientation clip mounted to a thermal blanket. Brackets for mounting the fire detection system sensing wires are positioned on the orientation clip, and the fastening system fixes the bracket to the IFS and traps the thermal blanket therebetween.

Mounting system for a nacelle fire detection system

There is disclosed a cork screw made up of a spiral screw for driving into a cork to thereby remove the cork from a bottle. The spiral screw is attached to a handle for driving the spiral screw into the cork. The handle passes through a flange that, along with a cork screw stop, provides a countervailing force as the spiral screw is used to drive a cork back into a bottle. An upper stop, integral to the cork screw is included. The upper stop maintains the position of the cork screw relative to the bottle as the cork is being removed from the bottle using the spiral screw. A lower stop, integral to the cork screw is also included. This lower stop maintains the position of the cork screw relative to the bottle as the cork is being returned to the bottle using the spiral screw.

Cork screw

A gutter insert for preventing the clogging of gutters and devices that are used for conducting a fluid to a desired location. The gutter insert can be connected end-to-end to produce a modular gutter insert having a desired length for placement in a gutter or like device. Closed ends on each segment of the modular gutter insert provide a plurality of internal screens for preventing debris from flowing towards downstream gutter downspouts and outlets.

Growing community of inventors

San Diego, CA, United States of America

Aleksandar Ratajac