General Electric Company

Other

United States of America As Represented by the Secretary of the Air Force

Richard L Horvath

James C Przytulski

Robert J Corsmeier

Philip H Stoughton

Christopher Charles Glynn

Richard Alan Wesling

Robert W Harris

James P Horvath

A necktie is disclosed. The necktie includes a knot portion that can be secured at or around a neck of a wearer. The knot portion includes a simulated knot having a front loop and a first attachment mechanism positioned on the simulated knot and covered by the front loop. The first attachment mechanism is accessible via an opening. The necktie also includes a blade portion. The blade portion includes a second attachment mechanism that can releasably attach to the first attachment mechanism.

Customizable necktie

A gas turbine engine has outer and inner counterrotatable annular turbine rotors and pluralities of turbine blades disposed in alternating rows and mounted on and extending between the respective rotors. An interstage seal arrangement for the engine is composed of a sequence of alternating inner and outer seals. Each outer seal is disposed between an interior side of the outer rotor and outer ends of the blades in one plurality thereof being spaced radially inward at their outer ends from the outer rotor and being mounted at their inner ends to the exterior side of the inner rotor. Each inner seal is disposed between the exterior side of the inner rotor and inner ends of the blades in another plurality thereof being spaced radially outward at their inner ends from the inner rotor and being mounted at their outer ends to the interior side of the outer rotor. Each inner seal is composed of an annular honeycomb component attached to the blade inner ends and a plurality of annular seal elements or teeth mounted on the exterior side of the inner rotor and projecting radially outwardly therefrom for sealably interfacing with the honeycomb component concurrently as the outer and inner rotors counterrotate relative to one another.

Interstage seal arrangement for airfoil stages of turbine engine

A gas turbine engine having an outer annular turbine rotor, which is counterrotatable relative to an inner annular turbine rotor, includes attachment structure for attaching turbine blades in circumferential rows to the inner rotor. The attachment structure includes first and second male members of hook-like configurations spaced axially along and circumferentially extending about the rotor, and first and second grooves defined by flanges attached to the rotor and axially spaced along and circumferentially extending about the rotor. The grooves open in a common axial direction for receiving in mated relation respectively and concurrently the hook-like configured first and second male members. The attachment structure also includes several different locking arrangements for locking the male members in mated relation with the grooves to thereby restrain the turbine blade against radial and axial movements relative to the rotor. Some locking arrangements are adapted for locking all of the blades but a last or final one thereof in a circumferential row around the rotor. Other locking arrangements are adapted for locking all of the blades in the circumferential row. Still other locking arrangements are adapted for locking only the last or final blade to complete the circumferential row of blades.

Turbine blade inner end attachment structure

A gas turbine engine having an outer annular turbine rotor, which is counterrotatable relative to an inner annular turbine rotor, includes attachment structure for attaching turbine blades in circumferential rows to the outer rotor. The attachment structure includes first and second male members spaced axially along and circumferentially extending about the rotor, and first and second grooves spaced axially along and extending circumferentially about the rotor being defined by flanges attached to the rotor. Each male member has a first portion attached to an end of a turbine blade and extending therefrom in a radial direction. The first male member has a second portion attached to its first portion and extending therefrom in an axial direction to define the first male member with an overall hook-like cross-sectional configuration. The first groove is cross-sectionally shaped for receiving in mated relation the second portion of the first male member. The second groove is cross-sectionally shaped for receiving in mated relation in the second groove a lock segment of the locking assembly and the first portion of the second male member to lock the male members in the respective grooves and thereby lock the turbine blade against radial and axial movements relative to the rotor.

Turbine blade outer end attachment structure

A corner level apparatus arranged for alignment of structural components at a corner intersection includes intersecting first and second arms, wherein the arms define an acute included angle therebetween, generally at forty-five degrees. A mount projects rearwardly of the junction for securement of a spirit level arranged parallel to a top surface of the first and second arms. A modification of the invention includes support legs telescopingly and adjustably mounted relative to a bottom surface of the arms projecting downwardly therefrom for support of the level structure for use as a gauge and a securement of various structural components at the corner intersection of a dwelling, wherein the apparatus in a further refinement includes chalk lines retractably mounted within each of the arms for alignment of the arms and use of the chalk line as a gauge in structural construction.

Corner level apparatus

An improved high pressure turbine rotor blade and tip cap structure therefor is provided which comprises a tip end closure for the blade bonded to the end wall of the blade casting and including a base plate member and a pair of upstanding side walls defining a peripheral contour coincidental with and faired to the cambered side walls of the casting, the base plate member having a plurality of radially outwardly opening passageways therethrough and disposed along the chord of the blade and communicating with a channel included in the radially outwardly facing surface of the casting along a chord of the blade, the passageways disposed along axes at angles to the base plate whereby coolant fluid flowing therethrough is directed against the tip side wall surfaces; and opening is provided through the end wall of the casting in the form of a slit or a plurality of holes along the chord of the blade and intersecting the channel, to define an outlet through the end wall for passage of coolant fluid through the blade.

One-piece HPTR blade squealer tip

An improved high pressure turbine rotor blade and tip cap structure therefor is provided, which comprises, a plurality of metallic layers bonded to the tip end of the blade, each layer having a peipheral shape conforming to the camber of the blade, the layers defining a plurality of radially outwardly opening, serpentine-shaped passageways for passage of coolant fluid through the periphery of the tip end of the blade.

Growing community of inventors

Hamilton, OH, United States of America

Richard L Horvath