Turbine rotor assemblies with improved slot cavities

Patent metadata

Field	Value
Publication number	US-9777575-B2
Application number	US-201414159043-A
Country	US
Kind code	B2
Filing date	Jan 20, 2014
Priority date	Jan 20, 2014
Publication date	Oct 3, 2017
Grant date	Oct 3, 2017

Abstract

The turbine rotor blade includes a platform with a first side and a second side; an airfoil extending from the first side of the platform; and an attachment portion extending from the second side of the platform. The attachment portion includes first and second side surfaces and a base surface on an underside of the attachment portion between the first and second side surface. The base surface includes at least one curved segment or angled segment.

First claim

What is claimed is:

1. A turbine rotor assembly for a turbine section of an engine, the turbine rotor assembly comprising:
a rotor disk with a plurality of slots formed about a periphery of the rotor disk, wherein a first slot of the plurality of slots includes a slot bottom and slot side walls; and
a first turbine rotor blade, comprising:
a platform with a first side and a second side;
an airfoil extending from the first side of the platform; and
an attachment portion extending from the second side of the platform and arranged within the first slot of the rotor disk, wherein the attachment portion includes first and second side surfaces and a base surface,
wherein the attachment portion includes feed inlets defined in the base surface for receiving cooling air, wherein the feed inlets include at least a first feed inlet and a second feed inlet, and

wherein the base surface and the slot bottom define a slot cavity with a slot inlet, the slot cavity configured to receive the cooling air through the slot inlet and direct the cooling air into the feed inlets,
wherein the slot cavity has a cross-sectional area that decreases along a generally axial direction, and wherein the first feed inlet is positioned at a first depth from the slot bottom wall to the first feed inlet, and the second feed inlet is positioned at a second depth from the slot bottom wall to the second feed inlet, and wherein the first depth is greater than the second depth, and
wherein the base surface includes a plurality of angled segments, each with a different slope, in between the first and second feed inlets.

2. The turbine rotor assembly of claim 1 , wherein the base surface includes at least one curved segment or at least one of the angled segments at each of the feed inlets and in between the feed inlets.

3. The turbine rotor assembly of claim 1 , wherein the base surface has a forward end and an aft end, and wherein the attachment portion has a first radial length between the platform and the forward end of the base surface and a second radial length between the platform and the aft end of the base surface, the second radial length being greater that the first radial length.

4. The turbine rotor assembly of claim 1 , wherein the feed inlets are scooped.

5. The turbine rotor assembly of claim 1 , wherein the base surface further includes at least one concave segment in between the first and second feed inlets.

6. The turbine rotor assembly of claim 1 , wherein the base surface further includes at least one convex segment in between the first and second feed inlets.

7. A turbine rotor assembly for a turbine section of an engine, the turbine rotor assembly comprising:
a rotor disk with a plurality of slots formed about a periphery of the rotor disk, wherein a first slot of the plurality of slots includes a slot bottom and slot side walls; and
a first turbine rotor blade, comprising:
a platform with a first side and a second side;
an airfoil extending from the first side of the platform; and
an attachment portion extending from the second side of the platform and arranged within the first slot of the rotor disk, wherein the attachment portion includes first and second side surfaces and a base surface,
wherein the attachment portion includes feed inlets defined in the base surface for receiving cooling air, wherein the feed inlets include at least a first feed inlet and a second feed inlet, and

wherein the base surface and the slot bottom define a slot cavity with a slot inlet, the slot cavity configured to receive the cooling air through the slot inlet and direct the cooling air into the feed inlets,
wherein the slot cavity has a cross-sectional area that decreases along a generally axial direction, and wherein the first feed inlet is positioned at a first depth from the slot bottom wall to the first feed inlet, and the second feed inlet is positioned at a second depth from the slot bottom wall to the second feed inlet, and wherein the first depth is greater than the second depth, and
wherein the base surface includes at least one concave segment in between the first and second feed inlets.

8. The turbine rotor assembly of claim 7 , wherein the base surface has a forward end and an aft end, and wherein the attachment portion has a first radial length between the platform and the forward end of the base surface and a second radial length between the platform and the aft end of the base surface, the second radial length being greater that the first radial length.

9. The turbine rotor assembly of claim 7 , wherein the base surface includes at least one convex segment in between the first and second feed inlets.

10. The turbine rotor assembly of claim 7 , wherein the feed inlets are scooped.

11. A turbine rotor assembly for a turbine section of an engine, the turbine rotor assembly comprising:
a rotor disk with a plurality of slots formed about a periphery of the rotor disk, wherein a first slot of the plurality of slots includes a slot bottom and slot side walls; and
a first turbine rotor blade, comprising:
a platform with a first side and a second side;
an airfoil extending from the first side of the platform; and
an attachment portion extending from the second side of the platform and arranged within the first slot of the rotor disk, wherein the attachment portion includes first and second side surfaces and a base surface,
wherein the attachment portion includes feed inlets defined in the base surface for receiving cooling air, wherein the feed inlets include at least a first feed inlet and a second feed inlet, and

wherein the base surface and the slot bottom define a slot cavity with a slot inlet, the slot cavity configured to receive the cooling air through the slot inlet and direct the cooling air into the feed inlets,
wherein the slot cavity has a cross-sectional area that decreases along a generally axial direction, and wherein the first feed inlet is positioned at a first depth from the slot bottom wall to the first feed inlet, and the second feed inlet is positioned at a second depth from the slot bottom wall to the second feed inlet, and wherein the first depth is greater than the second depth, and
wherein the base surface includes at least one convex segment in between the first and second feed inlets.

12. The turbine rotor assembly of claim 11 , wherein the base surface has a forward end and an aft end, and wherein the attachment portion has a first radial length between the platform and the forward end of the base surface and a second radial length between the platform and the aft end of the base surface, the second radial length being greater that the first radial length.

13. The turbine rotor assembly of claim 11 , wherein the feed inlets are scooped.

Assignees

• Honeywell Int Inc

Inventors

• Tapia Luis
• Halfmann Steve
• Harman Stuart Andrew

Classifications

• Y10T29/49321

  Assembling individual fluid flow interacting members, e.g., blades, vanes, buckets, on rotary support member · CPC title

• Y02T50/676

  Cross-Sectional Technologies · mapped topic

• F01D5/3007

  of axial insertion type · CPC title

• F01D5/081 Primary

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

• F01D5/04 Primary

  for radial-flow machines or engines · CPC title