Turbine rotor segmented sideplates with anti-rotation

Patent metadata

Field	Value
Publication number	US-10408087-B2
Application number	US-201514838880-A
Country	US
Kind code	B2
Filing date	Aug 28, 2015
Priority date	Nov 7, 2014
Publication date	Sep 10, 2019
Grant date	Sep 10, 2019

Abstract

A segmented sideplate for use in a gas turbine engine is described. The segmented sideplate includes a first plate having a first circumferential edge configured to interface with a complementary circumferential edge. The segmented sideplate also includes a second plate having a second circumferential edge configured to interface with the first circumferential edge.

First claim

What is claimed is:

1. A segmented sideplate to be positioned around an axis of rotation of a gas turbine engine, the segmented sideplate comprising:
a first plate having a first circumferential edge configured to interface with a complementary circumferential edge, a first outer diameter edge, and a first anti-rotation feature including a first protrusion and a second protrusion located circumferentially adjacent to the first protrusion, the first protrusion and the second protrusion each extending radially outward from the first outer diameter edge and being separated by a first middle segment of the first outer diameter edge such that a portion of a first airfoil engages with at least one of the first protrusion or the second protrusion in order to maintain a position of the first plate relative to the first airfoil; and
a second plate having a second circumferential edge configured to interface with the first circumferential edge, a second outer diameter edge, and a second anti-rotation feature including a third protrusion and a fourth protrusion located circumferentially adjacent to the third protrusion, the third protrusion and the fourth protrusion each extending radially outward from the second outer diameter edge and being separated by a second middle segment of the second outer diameter edge such that a portion of a second airfoil engages with at least one of the third protrusion or the fourth protrusion to maintain a position of the second plate relative to the second airfoil,
wherein the first circumferential edge and the second circumferential edge interface to form a void in a radial direction through which air may flow axially at a location radially outward from the first circumferential edge and the second circumferential edge.

2. The segmented sideplate of claim 1 , wherein:
the first circumferential edge includes a first joint feature; and
the second circumferential edge includes a second joint feature that is positioned at least partially adjacent the first joint feature in an axial direction.

3. The segmented sideplate of claim 2 , wherein the first joint feature and the second joint feature are shiplap edges.

4. The segmented sideplate of claim 2 , wherein the first plate and the second plate each have a first distance in the axial direction and the first joint feature and the second joint feature each have a second distance in the axial direction that is between 40% and 50% of the first distance.

5. The segmented sideplate of claim 2 , wherein the first joint feature and the second joint feature prevent air from flowing between the first plate and the second plate.

6. The segmented sideplate of claim 1 , wherein the segmented sideplate is configured to be used in a high pressure turbine section of the gas turbine engine.

7. The segmented sideplate of claim 1 , wherein:
the first plate further includes an inner diameter edge;
the first outer diameter edge includes a first outer segment separated from the first middle segment by the first protrusion; and
a first distance between the first middle segment of the first outer diameter edge and the inner diameter edge is greater than a second distance between the first outer segment of the first outer diameter edge and the inner diameter edge.

8. The segmented sideplate of claim 1 , wherein the first plate and the second plate define a concavity centered around an intersection of the first plate and the second plate such that the concavity may direct a flow of air radially outward from the concavity and axially aft through the concavity.

9. A gas turbine engine comprising:
a compressor section;
a combustor section; and
a turbine section including a segmented sideplate encircling an axis of rotation of the gas turbine engine, the segmented sideplate including:
a first plate having a first circumferential edge configured to interface with a complementary circumferential edge, a first outer diameter edge, and a first anti-rotation feature including a first protrusion and a second protrusion located circumferentially adjacent to the first protrusion, the first protrusion and the second protrusion each extending radially outward from the first outer diameter edge and being separated by a first middle segment of the first outer diameter edge such that a portion of a first airfoil engages with at least one of the first protrusion or the second protrusion in order to maintain a position of the first plate relative to the first airfoil, and

a second plate having a second circumferential edge configured to interface with the first circumferential edge, a second outer diameter edge, and a second anti-rotation feature including a third protrusion and a fourth protrusion located circumferentially adjacent to the third protrusion, the third protrusion and the fourth protrusion each extending radially outward from the second outer diameter edge and being separated by a second middle segment of the second outer diameter edge such that a portion of a second airfoil engages with at least one of the third protrusion or the fourth protrusion to maintain a position of the second plate relative to the second airfoil,
wherein the first circumferential edge and the second circumferential edge interface to form a void in a radial direction through which air may flow axially at a location radially outward from the first circumferential edge and the second circumferential edge.

10. The gas turbine engine of claim 9 , wherein:
the first plate has a first joint feature on the first circumferential edge; and
the second plate has a second joint feature on the second circumferential edge that is positioned at least partially adjacent the first joint feature in an axial direction.

11. The gas turbine engine of claim 10 , wherein the first joint feature and the second joint feature are shiplap edges.

12. The gas turbine engine of claim 10 , wherein the first plate and the second plate each have a first distance in the axial direction and the first joint feature and the second joint feature each have a second distance in the axial direction that is between 40% and 50% of the first distance.

13. The gas turbine engine of claim 10 , wherein the first joint feature and the second joint feature prevent air from flowing between the first plate and the second plate.

14. The gas turbine engine of claim 9 , wherein:
the first plate further includes an inner diameter edge;
the first outer diameter edge includes a first outer segment separated from the first middle segment by the first protrusion; and
a first distance between the first middle segment of the first outer diameter edge and the inner diameter edge is greater than a second distance between the first outer segment of the first outer diameter edge and the inner diameter edge.

15. The gas turbine engine of claim 9 , wherein the first plate and the second plate define a concavity centered around an intersection of the first plate and the second plate such that the concavity may direct a flow of air radially outward from the concavity and axially aft through the concavity.

Assignees

• United Technologies Corp

Inventors

• Snyder Daniel A
• Corcoran Christopher

Classifications

• F05D2250/712

  concave · CPC title

• F05D2250/184

  sinusoidal · CPC title

• F01D5/3015 Primary

  with side plates · CPC title

• F01D25/24 Primary

  Casings (modified for heating or cooling F01D25/14); Casing parts, e.g. diaphragms, casing fastenings (casings for rotary machines or engines in general F16M {; special arrangements in stators dealing with breaking-off of part of rotor F01D21/045}) · CPC title

• F02C3/04

  having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16) · CPC title