Abstract: A brush seal assembly is formed of a bristle array receiving at least one housing member. Alignment structures are formed on the housing and bristle assembly to ensure that the bristle assembly will be properly positioned in a working environment.

Abstract: In accordance with the present application, a fluid seal 30 and fluid sealing element 32, which are tolerant of fluid F direction reversals are provided. A sealing element 32 has at least two brush stages 50 to restrict leakage of the fluid F through a gap 38 between a component and a sealing surface. Each brush stage 50 includes a bristle arrangement 44 sandwiched between a back plate 48 and a common mid plate 46. A value allows 70 the fluid F to bypass a bristle arrangement 44 if the fluid pressure P1 or P2 varies between the chambers. Permanent damage to the sealing element 32 is avoided by allowing the higher pressure fluid F to bypass the upstream bristle arrangement 44 and a properly load the downstream bristle arrangement against a back plate 48.

Abstract: 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.

Abstract: A seal assembly includes a component of a gas turbine engine having a circumferential surface, a first knife edge seal, a second knife edge seal, and a brush seal assembly. The first knife edge seal and the second knife edge seal extend radially from the circumferential surface of the component and form a gap at the circumferential surface of the component between the first knife edge seal and the second knife edge seal. The brush seal assembly is positioned within the gap between the first knife edge seal and the second knife edge seal and is attached to the circumferential surface of the component.

Abstract: In accordance with the present application, a fluid seal 30 and fluid sealing element 32, which are tolerant of fluid F direction reversals are provided. A sealing element 32 has at least two brush stages 50 to restrict leakage of the fluid F through a gap 38 between a component and a sealing surface. Each brush stage 50 includes a bristle arrangement 44 sandwiched between a back plate 48 and a common mid plate 46. A value allows 70 the fluid F to bypass a bristle arrangement 44 if the fluid pressure P1 or P2 varies between the chambers. Permanent damage to the sealing element 32 is avoided by allowing the higher pressure fluid F to bypass the upstream bristle arrangement 44 and a properly load the downstream bristle arrangement against a back plate 48.

Abstract: 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.

Abstract: A brush seal assembly includes a plurality of bristles, a joint securing the bristles, and a retaining assembly. Each of the bristles has a first end and a second end. The joint has a first side and a second side and connects the first ends of the bristles. The retaining assembly sandwiches the joint and includes a side plate, a back plate, and a threaded connection. The side plate engages the first side of the joint and the back plate engages the second side of the joint. The threaded connection holds the side plate and the back plate in engagement with the joint.

Abstract: 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.

Abstract: A method of forming a brush seal which includes placing a bristle hoop sandwiched by a sideplate and a backplate in the cavity of a forming die. The components are then die formed together into a unitized brush seal.

Abstract: 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.

Abstract: A brush seal, comprising: a bristle arrangement having a retention section; a pair of plates flanking the bristle arrangement and having a clamping section to frictionally engage the retention section. The clamping section allows movement of the retention section before the plates are secured together, to place the bristle arrangement at a desired position between the plates, and prevents movement of the retention section after the plates are secured together.

Abstract: A brush seal assembly which includes a brush seal which is bristle hoop positioned between two plates. A segmented ring is positioned in contact with the brush seal and provides a uniform clamping force against the seal to hold it in place within a support member.

Abstract: A brush seal assembly for sealing a gap between a first component and a second component, comprising: a body; bristles extending from the body; and an extension from the body, the extension having an elongated slot therein. The slot, when the brush seal assembly mounts between the first and second components, allows the brush seal assembly to float within the gap. An axial brush seal assembly, comprising: a body; bristles extending from the body; and means for allowing movement of the brush seal assembly in an axial direction within the gap. An apparatus, comprising: a first component; a second component spaced from the first component in an axial direction; and an axial brush seal assembly movably mounted between the first and second components. The brush seal assembly can move in said axial direction.

Abstract: 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 the 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.

Abstract: A brush seal including a back plate, side plate and bristle ring is disclosed wherein the brush seal is secured together entirely through the use of removable fasteners. The back plate may be provided with a circumferential lip thereby providing a surface against which the head of a fastener can be used to compress the back plate against the side plate and thus capture the bristle ring therebetween. The brush seal can thereby be manufactured from disparate materials which could not be manufactured if welding were required.

Abstract: 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.

Abstract: A turbine engine has a rotor shaft rotatably carried within a non-rotating support structure. A seal is carried by the support structure circumscribing the shaft and having a flexible sealing element for sealing with the shaft. A chamber is located between the seal and support structure. A fluid is carried within the chamber and damps radial excursion of a seal axis from a support structure axis. The seal may be a full annulus or may be segmented. The fluid may be contained within one or more elastomeric bladders.

Abstract: A seal apparatus provides the seal between inner and outer elements. The seal apparatus has a flexible sealing element for forming a seal with a first of the inner and outer elements. At least one support element is secured to the sealing element. The seal further includes means for magnetically interacting with the first element to bias the seal relative to the first element.

Abstract: A turbine engine has a rotor shaft rotatably carried within a support structure. A seal is carried by the support structure circumscribing the shaft and having a brushpack for sealing with the shaft. A first plate on a first side of the brushpack has a first radial clearance from the rotor shaft. A rubplate has a radial clearance from the rotor shaft that is less than the first radial clearance when the seal and rotor are coaxial.

Abstract: A seal apparatus provides the seal between inner and outer elements. The seal apparatus has a flexible sealing element for forming a seal with a first of the inner and outer elements. At least one support element is secured to the sealing element. The seal further includes means for magnetically interacting with the first element to bias the seal relative to the first element.