US5333992A — Coolable outer air seal assembly for a gas turbin…

Claim 1

Independent Claim 211 words

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 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 min , the distance G min selected to permit cooling fluid to flow through the gap.

Claim 2

Dependent Claim 211 words

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 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 min , the distance G min selected to permit cooling fluid to flow through the gap.

Claim 3

Dependent Claim 67 words

The outer air seal assembly according to claim 1, wherein each of the seal segments further includes a channel extending circumferentially through the segment, the channel including an inlet and an outlet, the channel defining a cooling fluid flow passage, and wherein the means to flow cooling fluid directs cooling fluid into the inlet such that cooling fluid flows through the channel and exits through the outlet.

Claim 4

Dependent Claim 57 words

The outer air seal assembly according to claim 2, wherein each segment includes a plurality of circumferentially extending channels and a plurality of bumpers disposed on and extending circumferentially from the mating surface, wherein each bumper is disposed adjacent to one of the channels and wherein at least one of the channels is disposed between adjacent bumpers.

Claim 5

Dependent Claim 42 words

The outer air seal assembly according to claim 1, wherein the bumper extends radially between the radially outer surface of the segment and the radially inner surface of the segment, such that the bumper restricts fluid from flowing axially through the gap.

Claim 6

Dependent Claim 71 words

The outer air seal assembly according to claim 1, further including a feather seal which extends circumferentially between adjacent seal segments and axially over the clearance gap, and wherein the bumper further includes a ridge disposed radially outwardly of the channels and which extends axially along the mating surface and radially outwardly to a seal land, the ridge and seal land in conjunction defining a sealing edge for the feather seal.

Claim 7

Dependent Claim 42 words

The outer air seal assembly according to claim 3, wherein each bumper extends radially between the radially outer surface of the segment and the radially inner surface of the segment, such that the bumpers restricts fluid from flowing axially through the gap.

Claim 8

Dependent Claim 71 words

The outer air seal assembly according to claim 3, further including a feather seal which extends circumferentially between adjacent seal segments and axially over the clearance gap, and wherein the bumper further includes a ridge disposed radially outwardly of the channels and which extends axially along the mating surface and radially outward to a seal land, the ridge and seal land in conjunction defining a sealing edge for the feather seal.

Claim 9

Dependent Claim 57 words

The outer air seal assembly according to claim 6, wherein the bumper further includes a ridge disposed radially outwardly of the channels and which extends axially along the mating surface, such that the ridge restricts fluid from flowing radially outwardly through the gap and urges cooling fluid exiting the outlet to flow radially inwardly through the gap.

Claim 10

Dependent Claim 205 words

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 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 min , the distance G min selected to permit cooling fluid to flow through the gap.

Claim 11

Dependent Claim 205 words

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 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 min , the distance G min selected to permit cooling fluid to flow through the gap.

Claim 12

Dependent Claim 66 words

The gas turbine engine according to claim 9, wherein each of the seal segments further includes a channel extending circumferentially through the segment, the channel including an inlet and an outlet, the channel defining a cooling fluid flow passage, and wherein the means to flow cooling fluid directs cooling fluid into the inlet such that cooling fluid flows through the channel and exits through the outlet.

Claim 13

Dependent Claim 56 words

The gas turbine engine according to claim 10, wherein each segment includes a plurality of circumferentially extending channels and a plurality of bumpers disposed on and extending circumferentially from the mating surface, wherein each bumper is disposed adjacent to one of the channels and wherein at least one of the channels is disposed between adjacent bumpers.

Claim 14

Dependent Claim 41 words

The gas turbine engine according to claim 9, wherein the bumper extends radially between the radially outer surface of the segment and the radially inner surface of the segment, such that the bumper restricts fluid from flowing axially through the gap.

Claim 15

Dependent Claim 70 words

The gas turbine engine according to claim 9, further including a feather seal which extends circumferentially between adjacent seal segments and axially over the clearance gap, and wherein the bumper further includes a ridge disposed radially outwardly of the channels and which extends axially along the mating surface and radially outward to a seal land, the ridge and seal land in conjunction defining a sealing edge for the feather seal.

Claim 16

Dependent Claim 41 words

The gas turbine engine according to claim 11, wherein the bumper extends radially between the radially outer surface of the segment and the radially inner surface of the segment, such that the bumper restricts fluid from flowing axially through the gap.

Claim 17

Dependent Claim 70 words

The gas turbine engine according to claim 11, further including a feather seal which extends circumferentially between adjacent seal segments and axially over the clearance gap, and wherein the bumper further includes a ridge disposed radially outwardly of the channels and which extends axially along the mating surface and radially outward to a seal land, the ridge and seal land in conjunction defining a sealing edge for the feather seal.

Claim 18

Dependent Claim 56 words

The gas turbine engine according to claim 14, wherein the bumper further includes a ridge disposed radially outwardly of the channels and which extends axially along the mating surface, such that the ridge blocks fluid from flowing radially outwardly through the gap and urges cooling fluid exiting the outlet to flow radially inwardly through the gap.

Claim 19

Dependent Claim 157 words

A seal segment for a gas turbine engine having an outer air seal assembly, the outer air seal assembly having a plurality of the seal segments, each of the seal segments circumferentially spaced from adjacent seal segments to define a gap therebetween, the plurality of seal segments forming an annular structure, the gas turbine engine having a flowpath and including means to flow cooling fluid between adjacent seal segments, wherein the fluid flowing between adjacent segments flows radially inwardly and into the flow path, the seal segment including: a mating surface, the mating surface facing an adjacent seal segment of the outer air seal assembly; and a bumper disposed on and extending from the mating surface, the bumper having a height H b measured from the mating surface, the bumper defining means to maintain the gap at a minimum distance G min , the distance G min selected to permit cooling fluid to flow through the gap.

Claim 20

Dependent Claim 157 words

A seal segment for a gas turbine engine having an outer air seal assembly, the outer air seal assembly having a plurality of the seal segments, each of the seal segments circumferentially spaced from adjacent seal segments to define a gap therebetween, the plurality of seal segments forming an annular structure, the gas turbine engine having a flowpath and including means to flow cooling fluid between adjacent seal segments, wherein the fluid flowing between adjacent segments flows radially inwardly and into the flow path, the seal segment including: a mating surface, the mating surface facing an adjacent seal segment of the outer air seal assembly; and a bumper disposed on and extending from the mating surface, the bumper having a height H b measured from the mating surface, the bumper defining means to maintain the gap at a minimum distance G min , the distance G min selected to permit cooling fluid to flow through the gap.

Claim 21

Dependent Claim 59 words

The seal segment according to claim 17, further including a channel extending circumferentially through the segment, the channel including an inlet and an outlet, the channel defining a cooling fluid flow passage, and wherein the means to flow cooling fluid directs cooling fluid into the inlet such that cooling fluid flows through the channel and exits through the outlet.

Claim 22

Dependent Claim 55 words

The seal segment according to claim 18, wherein the segment includes a plurality of circumferentially extending channels and a plurality of bumpers disposed on and extending circumferentially from the mating surface, wherein each bumper is disposed adjacent to one of the channels and wherein at least one of the channels is disposed between adjacent bumpers.

Claim 23

Dependent Claim 47 words

The seal segment according to claim 17, wherein the bumper further includes a ridge disposed outwardly of the channels, and which extends along the mating surface and outwardly to a seal land, the ridge and seal land in conjunction defining a sealing edge for a feather seal.

Annuity Stage	Window Opens	Payment Deadline	Surcharge Period Until	Estimated Fee	Status
3.5 Years (Year 4)	1997-08-01	1998-01-31	1998-08-02	$2000.00	Window Closed / Lapsed
7.5 Years (Year 8)	2001-08-01	2002-01-31	2002-08-02	$3760.00	Window Closed / Lapsed
11.5 Years (Year 12)	2005-08-01	2006-01-31	2006-08-02	$7700.00	Window Closed / Lapsed

Coolable outer air seal assembly for a gas turbine engine

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