Air-cooled turbine rotor shroud with restraints

Claim 2

A stationary air-cooled shroud forming a portion of a turbine assembly and extending over and spaced from the tips of a plurality of blades of a rotor, said shroud comprising: an inner ring having a radially inner surface and a radially outer surface, said inner surface being juxtaposed to and spaced from the blade tips, said outer surface of the inner ring having a matrix of grooves provided therein; an outer restraining ring concentric with and surrounding the inner ring and covering said matrix of grooves to form a labyrinth of air-cooling passageways; and a suspension ring which cooperates with the inner ring and the outer restraining ring to define an entry flow path for the cooling air provided to the labyrinth, said suspension ring and outer restraining ring defining a plenum chamber for receiving cooling air, said plenum chamber being in communication with the entry flow path leading to the labyrinth whereby the passage of a flow of cool air through said labyrinth is operative to reduce the level and gradient of thermal expansion of the shroud for obtaining improved turbine blade tip clearance control.

Claim 3

A stationary air-cooled shroud forming a portion of a turbine assembly and extending over and spaced from the tips of a plurality of blades of a rotor as in claim 1 wherein said suspension ring and said inner ring are formed of a unitary member.

Claim 4

A stationary air-cooled shroud forming a portion of a turbine assembly and extending over and spaced from the tips of a plurality of blades of a rotor as in claim 1 wherein said matrix of grooves includes: a plurality of spaced circumferential grooves extending generally perpendicular to the longitudinal axis of the inner ring; and a plurality of interconnecting grooves extending generally parallel to the longitudinal axis of the inner ring, each interconnecting groove providing communication between two adjacent circumferential grooves.

Claim 5

A stationary air-cooled shroud forming a portion of a turbine assembly and extending over and spaced from the tips of a plurality of blades of a rotor as in claim 3 wherein said spaced circumferential grooves are parallel.

Claim 6

A stationary air-cooled shroud forming a portion of a turbine assembly and extending over and spaced from the tips of a plurality of blades of a rotor as in claim 3 wherein each circumferential groove is of constant cross-sectional configuration.

Claim 7

A stationary air-cooled shroud forming a portion of a turbine assembly and extending over and spaced from the tips of a plurality of blades of a rotor as in claim 3 wherein the cross-sectional areas of the circumferential grooves are substantially equal.

Claim 8

A stationary air-cooled shroud forming a portion of a turbine assembly and extending over and spaced from the tips of a plurality of blades of a rotor as in claim 3 wherein said matrix of grooves includes at least first, second, and third spaced parallel, circumferential grooves respectively extending from the upstream to the downstream portion of the shroud, and wherein said inner ring further includes a leading edge disposed adjacent the upstream portion of the shroud, said inner ring having metering apertures extending between said second circumferential groove and the leading edge of said inner ring for providing film cooling to the inner radial surface of said inner ring.

Claim 9

A stationary air-cooled shroud forming a portion of a turbine assembly and extending over and spaced from the tips of a plurality of blades of a rotor as in claim 3 wherein the interconnecting grooves extending between two adjacent pairs of circumferential grooves are staggered about the circumference of the inner ring.

Claim 10

A stationary air-cooled shroud forming a portion of a turbine assembly and extending over and spaced from the tips of a plurality of blades of a rotor as in claim 3 wherein said labyrinth includes a trailing edge portion from which the flow of cooling air exits the labyrinth, and wherein the interconnecting grooves at the trailing edge of the labyrinth are disposed at an angle to the longitudinal axis of the inner ring.

Claim 11

A stationary air-cooled shroud forming a portion of a turbine assembly and extending over and spaced from the tips of a plurality of blades of a rotor as in claim 1 wherein said inner ring is a unitary member.

Claim 12

A stationary air-cooled shroud forming a portion of a turbine assembly and extending over and spaced from the tips of a plurality of blades of a rotor as in claim 1 wherein the outer restraining ring is a unitary member.

Claim 13

A stationary air-cooled shroud forming a portion of a turbine assembly and extending over and spaced from the tips of a plurality of blades of a rotor as in claim 1 wherein the plenum chamber includes orifices for providing film cooling air to the space between the radially inner surface of the inner ring and the blade tips.

Claim 14

A stationary air-cooled shroud forming a portion of a turbine assembly and extending over and spaced from the tips of a plurality of blades of a rotor, said shroud comprising: an inner ring having a radially inner surface and a radially outer surface, said inner ring being juxtaposed to and spaced from the blade tips, said outer surface of the inner ring having a matrix of grooves provided therein, said matrix including a plurality of parallel, spaced circumferential grooves extending generally perpendicular to the longitudinal axis of the ring, and a plurality of interconnecting grooves extending generally parallel to the longitudinal axis of the inner ring, each interconnecting groove providing communication between two adjacent circumferential grooves; an outer restraining ring concentric with and surrounding the inner ring and covering said matrix of grooves to form a labyrinth of air-cooling passageways; and a suspension ring integral with said inner ring, which suspension ring cooperates with the inner ring and the outer restraint ring to define an entry flow path for providing cooling air to the labyrinth, said suspension ring and outer restraining ring defining a plenum chamber for receiving cooling air, said plenum chamber being in communication with the entry flow path leading to the labyrinth for providing cooling air to the labyrinth for reducing the level and gradient of thermal expansion of the shroud in order to obtain improved turbine blade tip clearance control.

Claim 15

A stationary air-cooled shroud forming a portion of a turbine assembly and extending over and spaced from the tips of a plurality of blades of a rotor, said shroud comprising: an inner ring having a radially inner surface and a radially outer surface, said inner ring being juxtaposed to and spaced from the blade tips, said outer surface of the inner ring having a matrix of grooves provided therein, said matrix including a plurality of parallel, spaced circumferential grooves extending generally perpendicular to the longitudinal axis of the ring, and a plurality of interconnecting grooves extending generally parallel to the longitudinal axis of the inner ring, each interconnecting groove providing communication between two adjacent circumferential grooves; an outer restraining ring concentric with and surrounding the inner ring and covering said matrix of grooves to form a labyrinth of air-cooling passageways; and a suspension ring integral with said inner ring, which suspension ring cooperates with the inner ring and the outer restraint ring to define an entry flow path for providing cooling air to the labyrinth, said suspension ring and outer restraining ring defining a plenum chamber for receiving cooling air, said plenum chamber being in communication with the entry flow path leading to the labyrinth for providing cooling air to the labyrinth for reducing the level and gradient of thermal expansion of the shroud in order to obtain improved turbine blade tip clearance control.

Claim 16

A stationary air-cooled shroud forming a portion of a turbine assembly and extending over and spaced from the tips of a plurality of blades of a rotor as in claim 13 wherein said suspension ring is a unitary member, said inner ring is a unitary member, and said outer restraining ring is a unitary member.

Claim 17

A stationary air-cooled shroud forming a portion of a turbine assembly and extending over and spaced from the tips of a plurality of blades of a rotor as in claim 13 wherein each circumferential groove is of constant cross-sectional configuration.

Claim 18

A stationary air-cooled shroud forming a portion of a turbine assembly and extending over and spaced from the tips of a plurality of blades of a rotor as in claim 13 wherein the cross-sectional areas of the circumferential grooves are substantially equal.

Claim 19

A stationary air-cooled shroud forming a portion of a turbine assembly and extending over and spaced from the tips of a plurality of blades of a rotor as in claim 13 wherein the interconnecting grooves extending between two adjacent pairs of circumferential grooves are staggered about the circumference of the inner ring.

Claim 20

A stationary air-cooled shroud forming a portion of a turbine assembly and extending over and spaced from the tips of a plurality of blades of a rotor as in claim 13 wherein said labyrinth includes a trailing edge portion from which the flow of cooling air exits the labyrinth, and wherein the interconnecting grooves at the trailing edge of the labyrinth are disposed at an angle to the longitudinal axis of the inner ring.

Claim 21

A stationary air-cooled shroud forming a portion of a turbine assembly and extending over and spaced from the tips of a plurality of blades of a rotor as in claim 13 wherein said plenum chamber includes an orifice for providing film cooling air to the space between the radially inner surface of the inner ring and the blade tips.

Claim 22

A stationary air-cooled shroud forming a portion of a turbine assembly and extending over and spaced from the tips of a plurality of blades of a rotor, said shroud comprising: an inner ring having a radially inner surface and a radially outer surface, said inner surface being juxtaposed to and spaced from the blade tips, said outer surface of the inner ring having a matrix of grooves provided therein, said matrix including at least first, second, and third spaced, parallel circumferential grooves extending generally perpendicular to the longitudinal axis of the inner ring from the upstream to the downstream portion of the shroud, and a plurality of interconnecting grooves extending generally parallel to the longitudinal axis of the inner ring, each interconnecting groove providing communication between two adjacent circumferential grooves, and wherein said inner ring further includes a leading edge disposed adjacent the upstream portion of the shroud, said inner ring having metering apertures extending between said second circumferential groove and the leading edge of the inner ring for providing film cooling to the inner radial surface of said inner ring; an outer restraining ring concentric with and surrounding the inner ring and covering said matrix of grooves to form a labyrinth of air-cooling passageways; and a suspension ring which cooperates with the inner ring and the restraint ring to provide an entry flow path for the cooling air provided to the labyrinth, whereby the passage of a flow of cool air through said labyrinth is operative to reduce the level and gradient of thermal expansion of the shroud for obtaining improved turbine blade tip clearance control.

Claim 23

A stationary air-cooled shroud forming a portion of a turbine assembly and extending over and spaced from the tips of a plurality of blades of a rotor, said shroud comprising: an inner ring having a radially inner surface and a radially outer surface, said inner surface being juxtaposed to and spaced from the blade tips, said outer surface of the inner ring having a matrix of grooves provided therein, said matrix including at least first, second, and third spaced, parallel circumferential grooves extending generally perpendicular to the longitudinal axis of the inner ring from the upstream to the downstream portion of the shroud, and a plurality of interconnecting grooves extending generally parallel to the longitudinal axis of the inner ring, each interconnecting groove providing communication between two adjacent circumferential grooves, and wherein said inner ring further includes a leading edge disposed adjacent the upstream portion of the shroud, said inner ring having metering apertures extending between said second circumferential groove and the leading edge of the inner ring for providing film cooling to the inner radial surface of said inner ring; an outer restraining ring concentric with and surrounding the inner ring and covering said matrix of grooves to form a labyrinth of air-cooling passageways; and a suspension ring which cooperates with the inner ring and the restraint ring to provide an entry flow path for the cooling air provided to the labyrinth, whereby the passage of a flow of cool air through said labyrinth is operative to reduce the level and gradient of thermal expansion of the shroud for obtaining improved turbine blade tip clearance control.

Claim 24

A stationary air-cooled shroud forming a portion of a turbine assembly and extending over and spaced from the tips of a plurality of blades of a rotor as in claim 20 wherein said inner ring is a unitary member, said outer restraining ring is a unitary member, and said suspension ring is a unitary member.

Claim 25

A stationary air-cooled shroud forming a portion of a turbine assembly and extending over and spaced from the tips of a plurality of blades of a rotor as in claim 20 wherein each circumferential groove is of constant cross-sectional configuration.

Claim 26

A stationary air-cooled shroud forming a portion of a turbine assembly and extending over and spaced from the tips of a plurality of blades of a rotor as in claim 20 wherein the cross-sectional areas of the circumferential grooves are substantially equal.

Claim 27

A stationary air-cooled shroud forming a portion of a turbine assembly and extending over and spaced from the tips of a plurality of blades of a rotor as in claim 20 wherein the interconnecting grooves extending between two adjacent pairs of circumferential grooves are staggered about the circumference of the inner ring.

Claim 28

A stationary air-cooled shroud forming a portion of a turbine assembly and extending over and spaced from the tips of a plurality of blades of a rotor as in claim 20 wherein said labyrinth includes a trailing edge portion from which the flow of cooling air exits the labyrinth, and wherein the interconnecting grooves at the trailing edge of the labyrinth are disposed at an angle to the longitudinal axis of the inner ring.