US 5,333,992 AGranted

Coolable outer air seal assembly for a gas turbine engine

AssigneeUnited Technologies Corporation

InventorsDaniel E. Kane, Donald E. Haddad

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Abstract

A coolable outer air seal assembly for a gas turbine engine is disclosed. Various construction details are developed which provide an outer air seal assembly comprised of a plurality of seal segments including bumpers adapted to maintain adequate cooling fluid flow through the clearance gap between adjacent seal segments. In one particular embodiment, each seal segment includes a mating surface having a plurality of bumpers disposed adjacent to cooling fluid channel outlets and an axially extending ridge disposed along the radially outer edge of the mating surface. The bumpers extend circumferentially a distance H.sub.b to maintain a minimum opening G.sub.min between adjacent seal segments and extend a radial distance W.sub.b to restrict fluid from flowing axially through the clearance gap. The ridge extends radially outward to define in part a seal edge for engaging a feather seal.

Claims20

Dependent claims

The outer air seal assembly for a gas turbine engine, the gas turbine engine disposed about a longitudinal axis and including an axially disposed flow path and a rotor assembly having a plurality of rotor blades engaged with working fluid within the flow path and adapted to rotate about the longitudinal axis, each rotor blade including a radially outer tip, the outer air seal assembly blocking working fluid from flowing radially outwardly of the rotor blades, the outer air seal assembly including:

a plurality of seal segments, each of the seal segments circumferentially spaced from an adjacent seal segment to define a gap therebetween, each segment having a mating surface facing the adjacent seal segment, the plurality of seal segments forming an annular structure disposed radially outwardly of the rotor assembly, each seal segment including a bumper disposed on and extending circumferentially from the mating surface, the bumper having a height H.sub.b measured circumferentially from the mating surface;
and
means to flow cooling fluid between adjacent seal segments;
wherein the fluid flowing between adjacent segments flows radially inwardly and into the flow path, wherein the bumper maintains the gap at a minimum distance G.sub.min, the distance G.sub.min selected to permit cooling fluid to flow through the gap.

1 more element

A gas turbine engine of the type disposed about a longitudinal axis and including an axially disposed flow path, a rotor assembly having a plurality of rotor blades engaged with working fluid within the flow path and adapted to rotate about the longitudinal axis, each rotor blade including a radially outer tip, and an outer air seal assembly blocking the working fluid from flowing radially outward of the blades wherein the outer air seal assembly includes:

a plurality of seal segments, each of the seal segments circumferentially spaced from an adjacent seal segment to define a gap therebetween, each segment having a mating surface facing the adjacent seal segment, the plurality of seal segments forming an annular structure disposed radially outwardly of the rotor assembly, each seal segment including a bumper disposed on and extending circumferentially from the mating surface, the bumper having a height H.sub.b measured circumferentially from the mating surface;
and
means to flow cooling fluid between adjacent seal segments;
wherein the fluid flowing between adjacent segments flows radially inwardly and into the flow path, wherein the bumper maintains the gap at a minimum distance G.sub.min, the distance G.sub.min selected to permit cooling fluid to flow through the gap.

1 more element

Dependencies are inferred from the claim text.