Axially-split radial turbines

Patent metadata

Field	Value
Publication number	US-9726022-B2
Application number	US-201514713220-A
Country	US
Kind code	B2
Filing date	May 15, 2015
Priority date	Apr 11, 2012
Publication date	Aug 8, 2017
Grant date	Aug 8, 2017

Abstract

Embodiments of an axially-split radial turbine, as are embodiments of a method for manufacturing an axially-split radial turbine. In one embodiment, the method includes the steps of joining a forward bladed ring to a forward disk to produce a forward turbine rotor, fabricating an aft turbine rotor, and disposing the forward turbine rotor and the aft turbine rotor in an axially-abutting, rotationally-fixed relationship to produce the axially-split radial turbine.

First claim

What is claimed is:

1. An axially-split radial turbine, comprising:
a forward turbine rotor, comprising:
a forward bladed ring; and
a forward disk joined to the forward bladed ring; and

an aft turbine rotor;
a plurality of hub flow paths extending from the forward turbine rotor to the aft turbine rotor, the plurality of hub low paths each comprising:
a leading portion defined, at least in substantial part, by the forward disk; and
an intermediate portion defined, at least in substantial part, by the forward bladed ring;

wherein the forward turbine rotor and the aft turbine rotor are disposed in an axially-abutting, rotationally-fixed relationship.

2. The axially-split radial turbine of claim 1 wherein the forward bladed ring comprises a plurality of forward bladed pieces, and wherein the plurality of forward bladed pieces are cast to include a plurality of blade cooling passages.

3. The axially-split radial turbine of claim 2 wherein the aft turbine rotor comprises an aft disk; and
wherein the axially-split radial turbine rotor further comprises an inner disk cavity formed between the forward disk and the aft disk, the inner disk cavity in fluid communication with the plurality of blade cooling passages, the inner disk cavity at least partially bound by the forward bladed ring, the forward disk, and the aft turbine rotor.

4. The axially-split radial turbine of claim 3 further comprising at least one hub cooling passage extending from an inner circumferential surface of the axially-split radial turbine to the inner disk cavity.

5. The axially-split radial turbine of claim 1 wherein the forward bladed ring is produced from a plurality of forward bladed pieces, the plurality of forward bladed pieces individually cast and metallurgically consolidated utilizing a direct thermal growth process to produce the forward bladed ring.

6. The axially-split radial turbine of claim 5 wherein the plurality of forward bladed pieces are each cast from a single crystal superalloy, and wherein the forward disk is produced from a non-single crystal superalloy.

7. An axially-split radial turbine comprising:
a forward turbine rotor, comprising:
a forward disk; and
a forward bladed ring circumscribing and metallurgically bonded to the forward disk at a bond line that terminates adjacent axially opposed end portions of the forward turbine rotor, as taken along a rotational axis of the axially-split radial turbine; and

an aft turbine rotor disposed axially adjacent to and rotationally fixed relative to the forward turbine rotor;
wherein the forward bladed ring comprises a plurality of forward bladed pieces, and wherein each of the plurality of forward bladed pieces is individually cast to include at least one forward blade segment.

8. The axially-split radial turbine of claim 7 further comprising:
a plurality of blade cooling passages extending in the plurality of forward bladed pieces; and
an inner disk cavity formed within the axially-split radial turbine and in fluid communication with the plurality of blade cooling passages.

9. The axially-split radial turbine of claim 7 wherein the plurality of forward bladed pieces are individually cast from a single crystal alloy, and wherein the forward disk is composed of a non-single crystal alloy.

10. The axially-split radial turbine of claim 7 wherein the aft turbine rotor comprises:
an aft bladed ring produced from a plurality of aft bladed pieces each including at least one aft blade segment; and
an aft disk joined to the aft bladed ring.

11. The axially-split radial turbine of claim 10 further comprising:
a plurality of blade cooling passages extending in the plurality of aft bladed pieces; and
an inner disk cavity formed within the axially-split radial turbine and in fluid communication with the plurality of blade cooling passages.

12. The axially-split radial turbine of claim 7 wherein the bond line has a generally conical geometry, which decreases in outer diameter when moving in a fore-aft direction.

13. The axially-split radial turbine of claim 7 further comprising a hub flow path extending over the aft and forward turbine rotors, the hub flow path having a leading portion defined by the forward disk and having an intermediate portion defined by the forward bladed ring.

14. An axially-split radial turbine, comprising:
an aft turbine rotor, comprising:
an aft disk; and
an aft bladed ring circumscribing and metallurgically bonded to the aft disk at a bond line that terminates adjacent axially opposed end portions of the aft turbine rotor, as taken along a rotational axis of the axially-split radial turbine; and

a forward turbine rotor disposed axially adjacent to and rotationally fixed relative to the aft turbine rotor;
wherein the aft bladed ring comprises a plurality of aft bladed pieces, and wherein each of the plurality of aft bladed pieces is individually cast to include at least one aft blade segment.

15. The axially-split radial turbine of claim 14 wherein the plurality of aft bladed pieces are individually cast from a single crystal alloy, and wherein the aft disk is composed of a non-single crystal alloy.

16. The axially-split radial turbine of claim 14 wherein the forward turbine rotor comprises:
a forward bladed ring produced from a plurality of forward bladed pieces each including at least one forward blade segment; and
a forward disk joined to the forward bladed ring.

17. The axially-split radial turbine of claim 16 wherein the plurality of forward bladed pieces include a plurality of blade cooling passages.

18. The axially-split radial turbine of claim 17 further comprising an inner disk cavity formed between the forward disk and the aft disk, the inner disk cavity in fluid communication with the plurality of blade cooling passages.

Assignees

• Honeywell Int Inc

Inventors

• Mittendorf Don
• Jan David K
• Smoke Jason
• Miner Amandine

Classifications

• Y10T29/49323

  Assembling fluid flow directing devices, e.g., stators, diaphragms, nozzles · CPC title

• Y10T29/49321

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

• F01D5/147 Primary

  Construction, i.e. structural features, e.g. of weight-saving hollow blades (F01D5/148, F01D5/16 and F01D5/20 take precedence; blade shape F01D5/141; blades with cooling or heating channels or cavities F01D5/18; heating, heat-insulating or cooling means on blades F01D5/18) · CPC title

• F01D5/066

  Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps · CPC title

• F01D5/04 Primary

  for radial-flow machines or engines · CPC title