United Technologies Corporation

General Electric Company

Brian Ellis Clouse

David P Dube

Paul W Baumann

David F Cloud

Donna Clough

Becky E Rose

Charles H Warner

Michael Hogan

Mark E Simonds

Craig Robert Jacobson

Louis M Cardoso

Myron Daniel Toomey

Robert Armstrong Morse

A blade outer air seal (BOAS) for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a seal body having a radially inner face and a radially outer face that axially extend between a leading edge portion and a trailing edge portion. A retention flange extends from the leading edge portion and a leaf seal contacts the retention flange.

Blade outer air seal with secondary air sealing

An outer air seal includes a seal wall, a heat shield, a side wall and a blade seal disposed radially inward of the seal wall. The seal wall has axially opposed first and second ends. The heat shield is radially outward of the seal wall and has first and second ends axially opposed ends. The second end of the heat shield is joined to the second end of the seal wall. The side wall is between the seal wall and the heat shield and spaces the first ends of the heat shield and the seal wall apart to form an inner cavity therebetween. Inner and outer diameter ends of the side wall are joined to the first ends of the seal wall and of the heat shield, respectively. The heat shield is configured to thermally isolate an outer case from the inner cavity and the seal wall.

Heat shields for air seals

A blade outer air seal (BOAS) for a gas turbine engine, according to an exemplary aspect of the present disclosure includes, among other things a seal body having a radially inner face and a radially outer face that axially extend between a leading edge portion and a trailing edge portion and a shiplap structure that at least partially overlaps at least a portion of at least one of the leading edge portion and the trailing edge portion.

Blade outer air seal having shiplap structure

A blade outer air seal (BOAS) for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a seal body having a radially inner face and a radially outer face that axially extend between a leading edge portion and a trailing edge portion and a seal land that extends from the seal body and includes an inward pointing extension that extends radially inwardly from the radially inner face.

Blade outer air seal having inward pointing extension

A diffuser seal for an aft end of a high pressure compressor of a gas turbine engine is disclosed. The diffuser seal includes a flow guide carrier coupled to the diffuser case. The flow guide carrier is also coupled to a static seal. The static seal engages a rotary seal and permits air flow through the static and rotary seals in the aft direction. The flow guide carrier is also coupled to a fairing and a fairing/hub support. The flow guide carrier supports the fairing in a spaced-apart position with respect to the rear hub so that air flowing through the static and rotary seals passes between a forward surface of the fairing and the rear hub. The fairing/hub support extends forward from the flow guide support and engages an aft surface of the fairing thereby limiting movement of the rear hub and fairing in the aft direction. This design helps to prevent parts or debris from piercing the rear hub and entering the high pressure turbine in the even of a fan blade-out or fan blade-off event.

Diffuser seal for geared turbofan or turboprop engines

The sealing apparatus and method of assembling the same is disclosed. The sealing apparatus may comprise a resilient member and a sealing member. The resilient member may define a cavity having a closed end and an open end. The resilient member may include a first wall having a first inner sealing surface and a second wall having a second inner sealing surface. The first and second walls may be joined at the closed end. The sealing member may be disposed at least partially in the cavity in sealing engagement with the first and second inner sealing surfaces. The sealing member may comprise an upper plurality of layered finger seals and a lower plurality of layered finger seals.

Duplex finger seal for joints with high relative displacement

A blade outer air seal (BOAS) for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a seal body having a radially inner face and a radially outer face that axially extend between a leading edge portion and a trailing edge portion. At least one of the leading edge portion and the trailing edge portion includes a solid wall and a perforated wall. At least a portion of the perforated wall is spaced from the solid wall such that a passage extends between the solid wall and the perforated wall.

Blade outer air seal having anti-rotation feature

An adapter to permit borescope access inside a gas turbine engine including a compressor stator having a plurality of compressor stator segments comprises a body portion defining a bore extending longitudinally therethrough from a first end to be disposed adjacent to outside surfaces of adjacent compressor stator segments to a second end to be disposed adjacent to inside surfaces of adjacent compressor stator segments. The bore permits a borescope to enter therethrough. The adapter further comprises an attachment portion for circumferentially coupling at least one compressor stator segment to an outer casing of the gas turbine engine.

Borescope inspection port device for gas turbine engine and gas turbine engine using same

An example variable stator vane assembly includes at least one button, a vane airfoil adjacent to the button, and a fillet defined between the button and the airfoil. In one example, the fillet defines a constant radius and extends beyond the button at least greater than a distance of 60% of a length of an overhang portion of the vane airfoil.

Variable compressor stator vane having extended fillet

A damper for a stator assembly, the stator assembly comprising a stator segment and a seal mounted to the stator segment. The damper locates between the stator segment and the seal, and comprises: a medial section; and opposed arms extending from the medial section. The medial section engages one of the stator segment and the seal and the opposed arms engage the other of the stator segment and the seal. A method of making the damper, comprising the steps of: providing a sheet of material having a medial section and opposed arms extending from the medial section; forming a bend at the medial section so that the medial section can engage one of the stator segment and the seal; and forming a bend at each of the arms so that the arms can engage the other of the stator segment and the seal.

Damper for stator assembly

A stator case for a gas turbine engine having a stator and a rotor. The rotor has a plurality of circumferential rows of blades. Each blade extends radially outward from a root to a tip. The case includes a tubular shell extending axially between a forward end and an aft end. The shell has an interior surface defining a hollow interior sized and shaped for receiving at least a portion of the rotor of the gas turbine engine. The case also includes a circular forward flange extending radially outward from the forward end of the shell and a circular aft flange extending radially outward from the aft end of the shell. In addition, the case includes a circular rib extending radially outward from the shell between adjacent rows of blades. The rib is sized and shaped for adjusting transient deflections of the shell to generally match transient deflections of the tips of the plurality of rotor blades to reduce a transient clearance between the interior surface of the tubular shell and the tips of the rotor blades.

Gas turbine engine stator case

A frangible cover is provided for a recess in a containment case for turbofan engine blade removal and access. The recess provided in the containment case allows outward radial movement of the engine fan blade when the engine fan blade is to be removed from the containment case. The present invention proposes a frangible component to cover the recess. A plurality of initiation points, notched in the frangible cover at intersections of surfaces encourages brittle fracture of the frangible component.

Growing community of inventors

Saugus, MA, United States of America

Brian Ellis Clouse