Turbine dovetail slot heat shield

Patent metadata

Field	Value
Publication number	US-10094228-B2
Application number	US-201514702097-A
Country	US
Kind code	B2
Filing date	May 1, 2015
Priority date	May 1, 2015
Publication date	Oct 9, 2018
Grant date	Oct 9, 2018

Abstract

Gas turbine engine turbine blade assembly includes a hollow airfoil joined to blade root, dovetail slot heat shield bonded or attached to a bottom surface of the root, and a shield outlet from heat shield open to inlet apertures extending radially through a radially inner root end of the root. Heat shield may have body with legs extending upwardly from heat shield bottom, slanted open upstream end, and free ends of the legs longer than the heat shield bottom. Flanges may be located along free ends and bonded to bottom surface. Body, heat shield bottom and/or the legs may be rounded. Disk includes a plurality of dovetail slots formed in a rim, complimentary plurality of turbine blades removably retained in dovetail slots by the roots, slot bottoms of the dovetail slots extending circumferentially between disk posts in rim. Heat shield bottoms may be radially spaced apart the slot bottoms.

First claim

What is claimed:

1. A gas turbine engine turbine blade assembly comprising:
a hollow airfoil integrally joined to a blade root,
a dovetail slot heat shield attached to and bonded to a bottom surface of the root, the heat shield including a body with a heat shield bottom and sides or legs extending upwardly or radially outwardly from the heat shield bottom, and
a shield outlet from the dovetail slot heat shield open to at least one inlet aperture extending radially through a radially inner root end of the root;
further comprising a slanted open forward or upstream end of the heat shield and free ends of the legs longer than the heat shield bottom.

2. A gas turbine engine turbine blade assembly comprising:
a hollow airfoil integrally joined to a blade root,
a dovetail slot heat shield attached to and bonded to a bottom surface of the root, the heat shield including a body with a heat shield bottom and sides or legs extending upwardly or radially outwardly from the heat shield bottom, and
a shield outlet from the dovetail slot heat shield open to at least one inlet aperture extending radially through a radially inner root end of the root;
further comprising an axially extending straight flange located along a free end of each of the legs and the flanges bonded to the bottom surface.

3. The assembly as claimed in claim 2 further comprising a slanted open forward or upstream end of the heat shield and the flanges and the free ends of the legs being longer than the heat shield bottom.

4. The assembly as claimed in claim 3 wherein the body is rounded.

5. The assembly as claimed in claim 4 further comprising the heat shield bottom and/or the legs are rounded.

6. A gas turbine engine turbine disk assembly comprising:
a disk including a web extending radially outwardly from a hub to a rim;
a plurality of dovetail slots in the rim;
a complimentary plurality of turbine blades removably retained in the plurality of dovetail slots;
slot bottoms of the dovetail slots and the dovetail slots extending circumferentially between disk posts in the rim on the disk, and
each of the turbine blades including a hollow airfoil integrally joined to a blade root, a dovetail slot heat shield attached to a bottom surface of the root, and a shield outlet from the dovetail slot heat shield open to at least one inlet aperture extending radially through a radially inner root end of the root;
wherein each heat shield is radially spaced from the slot bottom to create a clearance C between the heat shield and the slot bottom; and
the heat shield including a body with a heat shield bottom and sides or legs extending upwardly or radially outwardly from the heat shield bottom.

7. The assembly as claimed in claim 6 further comprising the heat shield being bonded to the bottom surface.

8. The assembly as claimed in claim 6 further comprising a slanted open forward or upstream end of the heat shield and free ends of the legs longer than the heat shield bottom.

9. The assembly as claimed in claim 6 further comprising:
an axially extending straight flange located along a free end of each of the legs,
the flanges bonded to the bottom surface,
a slanted open forward or upstream end of the heat shield, and
the flanges and the free ends of the legs being longer than the heat shield bottom.

10. The assembly as claimed in claim 6 wherein the body is rounded.

11. The assembly as claimed in claim 6 further comprising the heat shield bottom and/or the legs are rounded.

Assignees

• Gen Electric

Inventors

• Jendrix Richard William
• Schuppe Christopher Thomas
• Van Derven Christopher John
• Stoughton Samuel Joseph
• Mcmillan Charles Thomas
• Bibler John David

Classifications

• F01D5/3007 Primary

  of axial insertion type · CPC title

• F01D5/081

  Cooling fluid being directed on the side of the rotor disc or at the roots of the blades (F01D5/087 takes precedence) · CPC title

• F01D11/02 Primary

  by non-contact sealings, e.g. of labyrinth type (for sealing space between rotor blade tips and stator F01D11/08) · CPC title

• F01D5/30 Primary

  Fixing blades to rotors; Blade roots {; Blade spacers} · CPC title

• F01D25/08

  Cooling (of machines or engines in general F01P); Heating; Heat-insulation (of blade-carrying members, of blades F01D5/00) · CPC title