United Technologies Corporation

Mark E Addis

George H Reynolds

John A Szymbor

The present application discloses a method for repairing a damaged counterbore in a variable vane shroud. A layer of base material is removed from the vane shroud adjacent the counterbore such that a damaged portion of the counterbore is removed. A shrink-fit insert having a size slightly larger than that corresponding to the layer of base material removed from the shroud is placed into the area of removed material such that the counterbore is restored to pre-damaged dimensions upon installation of the shrink-fit insert.

Trunnion hole repair method utilizing interference fit inserts

The inventive method involves the inspection of a turbine engine. A damaged component of the turbine engine is identified. Portions of the turbine engine component are removed from the damaged area to accommodate an overlay. The overlay is sized smaller than the turbine engine component. The overlay is then placed in a location previously occupied by the removed portion and attached to the turbine engine component.

Method of repairing a turbine engine component

A vane shroud for a gas turbine engine has a cylindrical shaped body and a hole arranged at a circumference of the body. The hole is for receiving a trunnion from a variable vane. A counterbore is arranged concentrically around the hole on a radially inward facing surface of the body, and receives a trunnion hub from the variable vane. A shrink-fit insert is seated into the counterbore such that the trunnion hub is provided with a contact surface, and the shrink-fit insert is secured to the shroud through an interference fit.

Trunnion hole repair utilizing interference fit inserts

A brush seal assembly is disclosed that includes bristles arranged circumferentially about an axis to provide a bristle assembly. First and second plates are secured about the bristle assembly to provide a subassembly. A circumference of the subassembly is pressed into a retaining ring to provide the brush seal assembly. The circumference need not be machined. A perimeter weld is no longer needed to secure the first and second plates and bristle assembly to one another to provide the brush seal assembly.

Brush seal assembly and method of manufacturing same

A brush seal adapted to restrict a fluid flow through a gap between a first component and a second component, comprising: a body; a brush pack secured to the body; and a passage through the body for introducing a cooling flow to said gap. The passage has a first end that is exposed to the gap and a second end that is not exposed to the gap. The passage discharges a cooling flow to the brush seal, the cooling flow being discrete from the fluid flow.

Cooling arrangement for brush seal

A sealing assembly for a turbine engine has a brush configured to provide an air seal between an outer air seal segment and a blade. A support is provided for the brush and is configured for attachment to the outer air seal segment. The support is a flexible planar carrier having a first side and a second side. The brush extends from the first side while the second side is for attachment to the outer air seal segment. The flexible planar carrier has a stiffness less than a stiffness of the outer air seal segment.

Sealing assembly for a turbine engine

A brush seal includes a plurality of bristles aligned in parallel to form a brush pack having a first end and a second end, and a joint securing the brush pack together. The joint is located centrally between the first end and the second end such that both the first end and the second end of the brush pack can form a sealing surface.

Repairable double sided brush seal

The present invention relates to replaceable brush seal assemblies for use with turbines such as industrial gas turbines. In accordance with the present invention, a brush seal assembly comprises a flange, a brush seal mounted to the flange, and retainers preventing rotation of the brush seal relative to the flange. A method of repairing a brush seal having a back plate, side plate, and bristles is also disclosed. The method comprises the steps of removing the side plate and the bristles from the back plate, and securing a second brush seal to the back plate.

Replaceable brush seal elements

A brush seal, comprising: a bristle arrangement with a plurality of bristles; and a joint securing the bristles together; plates flanking the bristle arrangement; and a feature on the plates to receive the joint. A brush seal, comprising: a plurality of bristles, each having a first end and an opposed second end; and plates receiving the bristles therebetween, each having a first end and a second end. The first ends of the bristles extend past the first end of the plates and the second ends of the bristles reside between the first and second ends of the plates. A method of repairing a brush seal, comprising the steps of: providing a brush seal having a bristle arrangement secured between plates; removing the bristle arrangement from the plates; providing a replacement bristle arrangement; and placing said replacement bristle arrangement between the plates.

Brush seal

Disclosed are propulsion systemsproviding reduced fuel burn, weight and cost. A single gas generator coredrives multiple bladed propulsion elementswith a power train. The corehas a forward compressorand a rearward turbineand rotates about a longitudinal core axis. The bladed propulsion elementsrotate about bladed propulsion element axesthat are not coaxial with the core axis. The bladed propulsion elementsdischarge an ambient air streamrearward as a bypass streamportion and a core streamportion. The core streamportion is directed to the compressor. The propulsion systemsmount inside a fuselageof an airframeor they are suspended beneath a wingvia pylons

Aircraft propulsion systems

A variable vane shroud for a gas turbine engine comprises a cylindrically shaped body, a hole arranged at a circumference of the body, and a counterbore arranged concentrically around the hole on a radially inward facing surface of the body. The hole is for receiving a trunnion from a variable vane and the counterbore is for receiving a hub from the variable vane. A liner is inserted into the hole and counterbore such that the trunnion and hub are provided with a contact surface. The invention also provides a method for repairing a damaged counterbore in a variable vane shroud. A liner having a shape corresponding to a layer of material removed from the shroud is inserted into the void left by removing damaged material such that the counterbore is restored to pre-damaged dimensions.

Hole liners for repair of vane counterbore holes

A seal for restricting leakage of a fluid through a gap disposed between rotating and stationary components concentrically aligned within a gas turbine engine comprises a sealing member and a land. The sealing member is positioned on either the rotating or stationary component of the gas turbine engine and closes a gap between the rotating member and the stationary member. The land is positioned opposite the sealing member on either the rotating or stationary component of the gas turbine engine such that a clearance height is provided between the sealing member and the land. In one embodiment, the land is geometrically shaped according to expected changes in the gap and relative axial position of the sealing member and land during operation of the gas turbine engine. The sealing member and the land are positioned with respect to each other so that the clearance height is maintained approximately constant during operation of the gas turbine engine.

Passive air seal clearance control

A turbine engine includes a first turbine structure that supports a seal. The seal is movable within a recess of the first turbine structure. The seal is arranged in close proximity to a seal land of a second turbine structure for preventing a fluid from leaking past the seal and seal land. A thermal expansion member interconnects the first turbine structure and the seal. The thermal expansion member expands in response to an increase in temperature to move the seal toward the seal land preventing the typical enlarged gap between the seal and seal land resulting from thermal growth. In one example, the thermal expansion member, which is arranged at each opposing end of a seal segment, is a bimetallic coil spring supported on the first turbine structure by a cage. A free end of the coil spring is secured to the seal at the opposing end portions.

Seal for turbine engine

In accordance with the present application, a fluid sealand fluid sealing element, which are tolerant of fluid F direction reversals are provided. A sealing elementhas at least two brush stagesto restrict leakage of the fluid F through a gapbetween a component and a sealing surface. Each brush stageincludes a bristle arrangementsandwiched between a back plateand a common mid plate. A value allowsthe fluid F to bypass a bristle arrangementif the fluid pressure Por Pvaries between the chambers. Permanent damage to the sealing elementis avoided by allowing the higher pressure fluid F to bypass the upstream bristle arrangementand a properly load the downstream bristle arrangement against a back plate

Reverse flow tolerant brush seal

A method of making a bristle arrangement for a brush seal, which includes providing a bristle arrangement; severing the bristle arrangement, the bristle arrangement now having free ends; and joining the free ends. A method of reworking a bristle arrangement for a brush seal, which includes the steps of: providing a bristle arrangement; removing a section from the bristle arrangement; and adding a replacement section to the bristle arrangement.

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Kennebunk, ME, United States of America

Mark E Addis