A brush seal for gas turbine engines

A gas turbine engine (10) includes an axial brush seal (84) extending substantially axially between a vane support (48) and a plurality of blade outer air seals (62) to minimize leakage of cooler air into an air path (22) of working fluid. The axial seal (84) includes a first and a second rings (86,...

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Bibliographische Detailangaben
1. Verfasser:	BOUCHARD, JOSEPH P
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS CYLINDERS ENGINE PLANTS IN GENERAL ENGINEERING ELEMENTS AND UNITS GAS-TURBINE PLANTS GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVEFUNCTIONING OF MACHINES OR INSTALLATIONS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES PISTONS SEALINGS STEAM ENGINES THERMAL INSULATION IN GENERAL WEAPONS
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Beschreibung
Zusammenfassung:	A gas turbine engine (10) includes an axial brush seal (84) extending substantially axially between a vane support (48) and a plurality of blade outer air seals (62) to minimize leakage of cooler air into an air path (22) of working fluid. The axial seal (84) includes a first and a second rings (86, 88) extending axially with a plurality of bristles (92) sandwiched therebetween. Each of the plurality of bristles (92) includes a fore bristle end (98) and an aft bristle end (100) that come into contact with a vane support sealing surface (53) and a blade outer air seal sealing surface (76), respectively, with the bristles (92) being compressed against the sealing surfaces. The axial seal (84) is movable with respect to the vane support (48) and the blade outer air seals (62) to compensate for expansion and contraction of the vane support (48) and the plurality of blade outer air seals (62) as well as for lack of uniformity in the plurality of blade outer air seals.