초록

A unitary component for retaining a vane ring in a gas turbine engine comprises a retaining plate portion to restrain axial vane movement, a retaining ring portion to restrain circumferential vane movement, and a baffle portion to split a cooling air flow between the vane and an adjacent rotor.

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The invention claimed is: 1. A unitary component for retaining a vane ring in a gas turbine engine having an axis, the unitary component comprising a retaining plate portion to restrain axial vane movement, a retaining ring portion to restrain at least one of a circumferential vane movement and a r

The invention claimed is: 1. A unitary component for retaining a vane ring in a gas turbine engine having an axis, the unitary component comprising a retaining plate portion to restrain axial vane movement, a retaining ring portion to restrain at least one of a circumferential vane movement and a radial vane movement, and a baffle portion to split a cooling air flow between the vane and an adjacent rotor, wherein an annular sealing lip extends integrally axially aft from said mounting ring. 2. The unitary component as defined in claim 1, wherein the retaining plate portion and the retaining ring portion form part of a mounting ring having an axially facing surface in which a plurality of circumferentially spaced-apart lug slots are defined. 3. The unitary component as defined in claim 2, wherein each of said lug slots has a pair of radially extending side walls and a substantially closed axially facing base surface to provide an axially arresting surface for the vane ring. 4. The unitary component as defined in claim 2 wherein the lug slots only extend axially partly through the mounting ring. 5. The unitary component as defined in claim 2, wherein said baffle portion extends integrally radially inwardly from said mounting ring. 6. A turbine vane assembly for a gas turbine engine having an axis, comprising a one-piece vane ring mounted about an inner vane ring support via a tongue-and-groove joint, the tongue-and-groove joint including a plurality of blind grooves in an axially forwardly facing surface of the vane ring support and a plurality of corresponding lugs extending radially inwardly from the one-piece vane ring, the lugs being interconnected altogether by said one-piece vane ring, each blind groove having a pair of radially extending sidewalls projecting axially forwardly from an axially forwardly facing base surface of the groove, the lugs distributed along an inner circumference of the one-piece vane ring being received between corresponding radially extending sidewalls of the blind grooves, thereby cooperating altogether for restraining the vane ring against both circumferential and radial vane movement relative to the inner vane ring support. 7. The turbine vane assembly as defined in claim 6, wherein the inner vane ring support has a mounting ring portion in which said tongue-and-groove joint is provided and a turbine rotor front cavity baffle portion extending integrally radially inwardly from said mounting ring portion, the mounting ring portion and the turbine rotor front cavity baffle portion being of unitary construction. 8. The turbine vane assembly as defined in claim 7, wherein the baffle includes an annular rotor sealing lip. 9. The turbine vane assembly as defined in claim 6, wherein an annular sealing lip extends axially rearwardly from the inner vane ring support. 10. A turbine vane support for supporting a turbine vane ring in a gas turbine engine having an axis, comprising a mounting ring portion adapted to be coaxially mounted in the engine and having a series of circumferentially spaced-apart lug seats defined in a front surface of the mounting ring, each of said lug seats having a pair of radially extending sidewalls projecting from an axially forwardly facing base wall, and wherein the baffle extends radially inwardly from said mounting ring portion, said baffle and said mounting ring portion being integral, and wherein the baffle includes an annular rotor sealing lip. 11. The turbine vane support as defined in claim 10, wherein an annular sealing lip extends axially rearwardly from said mounting ring. 12. The turbine vane support as defined in claim 10, wherein a plurality of circumferentially spaced-apart blind slots are defined in said front surface of said mounting ring portion to form said lug seats. 13. A turbine vane support in combination with a one-piece turbine vane ring coaxially mounted about an axis, the one-piece turbine vane ring having a plurality of circumferentially spaced-apart vane lugs extending radially inwardly from a common inner annular band extending along a full turn, the inner vane ring support having a plurality of circumferentially spaced-apart blind slots defined in an axially forwardly facing surface thereof for receiving the vane lugs in a tongue-and-groove fashion, each blind slots having a pair of radially extending sidewalls defining a gap for receiving a corresponding one of said vane lugs therebetween and an axially forwardly facing surface, the lugs in the slots cooperating altogether to both circumferentially and radially restrained relative motion between the one-piece turbine vane ring and the turbine vane support. 14. The combination as defined in claim 13, wherein said blind slots are defined in a mounting ring portion of said inner vane ring support, and wherein a baffle extends integrally radially inwardly from said mounting ring portion. 15. The combination as defined in claim 13, wherein an annular sealing lip extends integrally axially rearwardly from said inner vane ring support. 16. A unitary vane ring for use with an annular support having a plurality of circumferentially spaced-apart blind slots defined in a front surface thereof, each of said blind slots having a pair of sidewalls projecting forwardly from an axially facing surface of the slot, the sidewalls defining a gap having a width (W1); the unitary vane ring comprising a plurality of circumferentially spaced-apart vanes having an airfoil portion extending radially between one-piece inner and outer annular bands, and a plurality of circumferentially spaced-apart vane lugs, each of said vane lugs having a pair of opposed side edges extending radially inwardly from said inner annular band, the vane lugs being circumferentially distributed along the inner annular band, the inner annular band forming a common base for said vane lugs, the side edges of said lugs being spaced by a width (W2) generally corresponding to the width (W1) of the blind slots, said vane lugs adapted to be received in tongue-and-groove engagement in said blind slots, and in circumferential arresting contact with the sidewalls of the blind slots-and cooperating altogether to restrain relative radial motion between the vane ring and the annular support.