Shroud ring for use in a gas turbine engine

• US 4,395,195 A
• Filed: 05/16/1980
• Issued: 07/26/1983
• Est. Priority Date: 05/16/1980
• Status: Expired due to Term

• Current Assignee: United Technologies Corporation (Rtx Corporation)
• Original Assignee: United Technologies Corporation (Rtx Corporation)
• Inventors: Young, John H., De Cosmo, Anthony R.
• Primary Examiner(s): Casaregola, Louis J.
• Assistant Examiner(s): Simenauer, Jeffrey A.
• Application Number:
  US06/150,489
• Time in Patent Office: 1,166 Days
• Field of Search: 415/134, 415/136, 415/137, 415/138, 415/139, 415/170 R, 415/172 R
• US Class Current: 415/137
• CPC Class Codes: F01D 11/001 for sealing space between stator blade and rotor
• CPC Class Codes: F01D 17/162 for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line F01D17/167 takes precedence
• CPC Class Codes: F01D 9/042 fixing blades to stators fixing stator-rings in the casing or to each other F01D25/246
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A shroud ring (22) for a gas turbine engine having a stator structure (14) and an array of inwardly extending stator vanes (20) is disclosed. The shroud ring is circumferentially segmented to accommodate inward and outward movement of the vanes and the stator structure. The shroud ring has a segmented outer ring (28) and a segmented inner ring (30). The outer ring engages the vanes to support the vanes and to position the inner ring and an integral seal member (24) about a rotor structure. In one embodiment the vanes (20) are rotatable about a spanwise axis S. In a second embodiment, the vanes (120) are integrally attached to the shroud ring (122).

Claims

1. For a gas turbine engine of the type having a stator structure outward of a flow path for working medium gases, rotor structure inward of the flow path for working medium gases and an array of stator vanes extending inwardly across the flow path from the outward stator structure into proximity with the inward rotor structure, an improved shroud ring for supporting the inward ends of the vanes and a seal member radially outwardly of the rotor structure, wherein the improvement comprises:

a first ring formed of a plurality of segments extending circumferentially, each segment spaced from an adjacent segment leaving a gap therebetween and each segment engaging at least two stator vanes at the inward end of the stator vane to support the stator vanes in guided cantilever fashion, each segment being adapted by a hole at each vane to receive the vane;

a second ring inwardly of the first ring, the second ring formed of a plurality of segments, each segment slidably engaging in the circumferential direction a corresponding segment of the first ring and each segment having an inner wall extending inwardly of the corresponding segment of the first ring to cover at least one of said holes in the corresponding segment which adapt said corresponding segment of the first ring to receive the stator vanes for blocking the leakage of working medium gases between the vanes and the first ring;

wherein the sliding engagement between the first ring and the second ring enables the stator structure to position the second ring radially about the rotor structure in response to inward and outward movement of the stator structure.

2. The shroud ring according to claim 1 wherein the seal member is formed of a plurality of circumferentially extending seal segments, and each segment is integrally attached to the corresponding segment of the second ring and each seal segment extends circumferentially beyond the end of the corresponding segment of the second ring.

3. The shroud ring according to claim 1 wherein the corresponding segment of the first ring is adapted to receive a plurality of vanes, each vane being rotatable about a spanwise axis with respect to the corresponding segment.

4. The assembly according to claim 1 wherein each vane has an airfoil, and wherein a plurality of plates are outward of the first ring such that a plate at each segment of the first ring engages the segment of the first ring and is integrally attached to the airfoil of at least one of the vanes engaged by the segment of the first ring.

5. The assembly according to claim 4 wherein each vane engaged by the segment of the first ring has an inwardly extending tab integrally attached to the segment of the first ring and wherein the plate engaged by the segment of the first ring is integrally attached to the segment of the first ring and the vanes engaged by the segment of the the first ring.

6. The assembly according to claim 4 wherein the plate is attached to a single vane, the plate is cylindrical and has a cylindrical tab extending inwardly adapted to receive a means for locking the vane in radial position with respect to the outer ring and wherein the segment of the ring is adapted to receive the cylindrical plate and the cylindrical tab and wherein a means for locking the vane in radial position with respect to the outer ring engages the cylindrical tab.

7. The assembly according to claim 6 wherein the vane has a spanwise axis and is rotatable about said axis.

8. The assembly according to claims 1, 2, 3, 4, 5, 6, or 7 wherein each segment of the second ring overlaps circumferentially a first segment of the first ring which is said corresponding segment and overlaps circumferentially a second segment of the first ring wherein the assembly further has a means for preventing circumferential movement of a segment of the second ring with respect to an adjacent second segment of the first ring and wherein said means engages the first ring and the second ring.

13. The shroud ring according to claim 1 wherein each segment of the second ring has an upstream sidewall extending radially from the inner wall and an upstream outer wall spaced radially from the inner wall which extends axially from the upstream sidewall over the first ring and further has a downstream sidewall extending radially from the inner wall and a downstream outer wall spaced radially from the inner wall which extends axially from the downstream sidewall over the first ring.

9. For a gas turbine engine of the type having a stator structure outward of a flow path for working medium gases, rotor structure inward of the flow path for working medium gases and an array of stator vanes extending inwardly across the flow path from the outward stator structure into proximity with the inward rotor structure, an improved shroud ring and vane assembly for supporting the inward ends of the vanes and a seal member radially outwardly of the rotor structure, wherein the improvement comprises:

a first ring formed of a plurality of segments extending circumferentially, each segment spaced from an adjacent segment leaving a gap therebetween and each segment adapted to engage at least two stator vanes at the inward end of the stator vane to support the stator vanes in guided cantilever fashion, each segment being adapted by a hole at each vane to receive

a second ring inwardly of the first ring, the second ring being formed of a plurality of segments, each segment slidably engaging in the circumferential direction a corresponding segment of the first ring and each segment having an inner wall extending inwardly of the corresponding segment of the first ring to cover at least one of said holes in the corresponding segment which adapt said corresponding segment of the first ring to receive the stator vanes for blocking the leakage of working medium gases between the vanes and the first ring;

wherein the sliding engagement between the first ring and the second ring adapts the stator structure to position the second ring radially about the rotor structure in response to inward and outward movement of the stator structure.

10. The shroud ring according to claim 9 wherein the seal member is formed of a plurality of circumferentially extending seal segments, and each segment is integrally attached to a corresponding segment of the second ring and each seal segment extends circumferentially beyond the end of the corresponding segment of the second ring.

11. The shroud ring according to claim 10 wherein each segment of the first ring is adapted to receive a plurality of vanes each vane being rotatable about a spanwise axis with respect to the corresponding segment.

12. The assembly according to claims 9, 10 or 11 wherein each segment of the second ring overlaps circumferentially a first segment of the first ring which is said corresponding segment and overlaps circumferentially a second segment of the first ring wherein the assembly further has a means for preventing circumferential movement of a segment of the second ring with respect to an adjacent second segment of the first ring and wherein said means engages the first ring and the second ring.