Blade feature to support segmented coverplate

Patent metadata

Field	Value
Publication number	US-10563525-B2
Application number	US-201415038536-A
Country	US
Kind code	B2
Filing date	Nov 5, 2014
Priority date	Dec 19, 2013
Publication date	Feb 18, 2020
Grant date	Feb 18, 2020

Abstract

A gas turbine engine component comprises a blade having a leading edge and a trailing edge. The blade is mounted to a disc and configured for rotation about an axis. A platform supports the blade, and has a fore edge portion at the leading edge and an aft edge portion at the trailing edge. At least one of the fore edge portion and aft edge portion includes a mouth portion defined by an inner wing and an outer wing spaced radially outward of the inner wing. At least one coverplate is retained against the disc by the inner wing. A gas turbine engine is also disclosed.

First claim

The invention claimed is:

1. A gas turbine engine component comprising:
a blade having a leading edge and a trailing edge, the blade mounted to a disc and configured for rotation about an axis;
a platform supporting the blade, the platform having a fore edge portion at the leading edge and an aft edge portion at the trailing edge, and wherein at least one of the fore edge portion and aft edge portion includes a mouth portion defined by an inner wing and an outer wing spaced radially outward of the inner wing, and wherein the inner wing includes a radially outer surface and a radially inner surface that extends in an aft direction and comprises a flat linear surface portion that is parallel to the axis, and wherein the inner wing includes a nub extending from the radially inner surface and an angled surface portion formed in the radially inner surface at an angle relative to the flat linear surface portion, and wherein the angled surface portion extends radially inward from a rear thrust face of the blade to a forward side of the nub, and wherein the flat linear surface portion extends from an aft side of the nub to a distal end of the inner wing; and
at least one coverplate retained against the disc by the inner wing, wherein an outer peripheral edge of the at least one coverplate is retained against the rear thrust face of the blade, and wherein a radial outer surface of the outer peripheral edge engages the angled surface portion of the inner wing.

2. The gas turbine engine component according to claim 1 wherein the nub extends from the radially inner surface of the inner wing in a direction toward the axis, the nub being spaced from the rear thrust face of the blade, and wherein the outer peripheral edge of the at least one coverplate is received within a pocket formed between the rear thrust face and the nub to retain the at least one coverplate against the disc.

3. The gas turbine engine component according to claim 2 wherein the radial outer surface of the outer peripheral edge engages the angled surface portion on the forward side of the nub.

4. The gas turbine engine component according to claim 3 wherein the angled surface portion is non-parallel to the axis and extends in a direction that is radially inward relative to the axis.

5. The gas turbine engine component according to claim 3 wherein the angle of the angled surface portion relative to the flat linear surface portion is greater than zero degrees.

6. The gas turbine engine component according to claim 2 wherein the at least one coverplate comprises a segmented coverplate portion that is part of a set of segmented coverplate portions that together form a first coverplate portion.

7. The gas turbine engine component according to claim 6 , wherein the at least one coverplate further includes a second coverplate portion that is located radially inward of the first coverplate portion.

8. The gas turbine engine component according to claim 7 wherein the second coverplate portion comprises a single-piece full hoop coverplate.

9. The gas turbine engine component according to claim 8 wherein the segmented coverplate portion includes the outer peripheral edge that is retained by the nub of the inner wing, and wherein the segmented coverplate portion includes an inner peripheral edge that is trapped against the disc by an outer peripheral edge of the full single-piece hoop coverplate.

10. The gas turbine engine component according to claim 8 wherein the single-piece full hoop coverplate is comprised of a nickel alloy material and the first coverplate portion is comprised of a titanium aluminum alloy material.

11. The gas turbine engine component according to claim 1 wherein the mouth portion is formed at the aft edge portion of the platform.

12. The gas turbine engine component according to claim 1 wherein the inner and outer wings are parallel to each other.

13. The gas turbine engine component according to claim 1 , wherein the at least one coverplate comprises a segmented coverplate portion and a full hoop coverplate portion, wherein the outer peripheral edge of the at least one coverplate comprises an outermost peripheral edge of the segmented coverplate portion, and wherein the segmented coverplate portion includes an innermost peripheral edge, and wherein the outermost peripheral edge engages the rear thrust face and the full hoop coverplate portion engages the innermost peripheral edge.

14. The gas turbine engine component according to claim 13 , wherein the full hoop coverplate portion includes a main body portion that extends radially inward toward the axis and an outer peripheral portion that extends transversely relative to the main body portion in a direction toward an aft end of the disc to terminate at an outer peripheral surface, and wherein the outer peripheral surface engages an aft face of the segmented coverplate portion to trap a forward face of the segmented coverplate portion directly against the rear thrust face.

15. A gas turbine engine component comprising:
a blade having a leading edge and a trailing edge, the blade mounted to a disc and configured for rotation about an axis;

a platform supporting the blade, the platform having a fore edge portion at the leading edge and an aft edge portion at the trailing edge, and wherein at least one of the fore edge portion and aft edge portion includes a mouth portion defined by an inner wing and an outer wing spaced radially outward of the inner wing, and wherein the inner wing includes a radially outer surface and a radially inner surface that extends in an aft direction and comprises a flat linear surface portion that is parallel to the axis, and wherein the inner wing includes a nub extending from the radially inner surface and an angled surface portion formed in the radially inner surface at an angle relative to the flat linear surface portion, and wherein the angled surface portion extends radially inward from a rear thrust face of the blade to a forward side of the nub, and wherein the flat linear surface portion extends from an aft side of the nub to a distal end of the inner wing; and
at least one coverplate retained against the disc by the inner wing, wherein a radial outer surface of an outer peripheral edge of the at least one coverplate engages the angled surface portion of the inner wing, and wherein the at least one coverplate comprises a first coverplate portion and a second coverplate portion located radially inward of the first coverplate portion, the first coverplate portion being made from a first material and the second coverplate portion being made from a second material different than the first material.

16. The gas turbine engine component according to claim 15 wherein the second material is a nickel alloy material and the first material is a titanium aluminum alloy material.

17. The gas turbine engine component according to claim 15 wherein the first coverplate portion comprises a segmented coverplate and the second coverplate portion comprises a full hoop coverplate.

18. The gas turbine engine component according to claim 15 wherein the nub extends from the radially inner surface of the inner wing in a direction toward the axis, the nub being spaced from the rear thrust face of the blade, and wherein the outer peripheral edge of the at least one coverplate is received within a pocket formed between the rear thrust face and the nub to retain the at least one coverplate against the disc, and wherein the angled surface portion is non-parallel to the axis and extends in a direction that is radially inward relat

Assignees

• United Technologies Corp

Inventors

• Hough Matthew Andrew
• Corcoran Christopher
• Beattie Jeffrey S

Classifications

• F01D5/3015 Primary

  with side plates · CPC title

• F01D25/005

  Selecting particular materials · CPC title

• F05D2220/32

  in gas turbines · CPC title

• Y02T50/671

  Cross-Sectional Technologies · mapped topic

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title