Vaneless counterrotating turbine

Patent metadata

Field	Value
Publication number	US-2016195010-A1
Application number	US-201514797264-A
Country	US
Kind code	A1
Filing date	Jul 13, 2015
Priority date	Jul 15, 2014
Publication date	Jul 7, 2016
Grant date	—

Abstract

A gas turbine engine includes a compressor section, a combustor, and a turbine section. The turbine section includes a first turbine portion and a second turbine portion, with the first and second turbine portions being counter-rotating turbine portions. A transition duct transitions fluid flow from the first turbine portion to the second turbine portion. The transition duct is a vaneless transition duct.

First claim

1 . A gas turbine engine comprising:
a compressor section; a combustor fluidly connected to the compressor section via a primary flowpath; a turbine section fluidly connected to the combustor via the primary flowpath, wherein the turbine section includes at least a first turbine portion and a second turbine portion connected to the first turbine portion via a transition duct, fluid in the second turbine portion having a lower pressure than fluid in the first turbine portion, and wherein the first turbine portion and the second turbine portion are counter-rotating turbine portions; wherein the second turbine portion includes at least three turbine stages; wherein the transition duct is vaneless; and wherein the first turbine portion and the second turbine portion are counter rotating turbine portions.

2 . The gas turbine engine of claim 1 , further comprising a static support structure disposed aft of a first stage of said second turbine portion and fore of a last stage of said second turbine portion.

3 . The gas turbine engine of claim 2 , wherein the static support structure is disposed between said first stage of the second turbine section and a second stage of the second turbine section.

4 . The gas turbine engine of claim 2 , wherein the static support structure is directly connected to an outer diameter of the primary flowpath and wherein the static support structure is connected to a second shaft via a bearing.

5 . The gas turbine engine of claim 1 , wherein the first turbine portion drives a first shaft and the second turbine portion drives a second shaft, and wherein the first shaft is supported relative to the second shaft via a piggyback intershaft bearing arrangement.

6 . The gas turbine engine of claim 1 , wherein the second turbine portion includes exactly three turbine stages.

7 . The gas turbine engine of claim 1 , further comprising a turbine exhaust case connected to a fluid exit of the second turbine portion.

8 . The gas turbine engine of claim 7 , wherein the turbine exhaust case is supported relative to a second shaft via at least a first support wall and a bearing.

9 . A gas turbine engine comprising:
a compressor portion; a combustor fluidly connected to the compressor portion; a turbine portion fluidly connected to the combustor, wherein the turbine portion includes at least a first turbine section and a second turbine section connected to the first turbine section via a transition duct, fluid in the second turbine section having a lower pressure than fluid in the first turbine section; wherein the second turbine section is a split turbine section and a static support structure is disposed within the split turbine section; and wherein the transition duct is vaneless.

10 . The gas turbine engine of claim 9 , wherein the second turbine section includes at least three turbine stages.

11 . The gas turbine engine of claim 9 , wherein the first turbine portion and the second turbine portion are counter rotating turbine portions.

12 . The gas turbine engine of claim 9 , wherein the static support structure is disposed between said first stage of the second turbine section and a second stage of the second turbine section.

13 . The gas turbine engine of claim 9 , wherein the static support structure is directly connected to an outer diameter of the primary flowpath and wherein the static support structure is connected to a second shaft via a bearing.

14 . The gas turbine engine of claim 9 , wherein the first turbine portion drives a first shaft and the second turbine portion drives a second shaft, and wherein the first shaft is supported relative to the second shaft via a piggy back bearing arrangement.

15 . The gas turbine engine of claim 9 , wherein the second turbine portion includes exactly three turbine stages.

16 . The gas turbine engine of claim 9 , further comprising a turbine exhaust case connected to a fluid exit of the second turbine portion.

17 . The gas turbine engine of claim 16 , wherein the turbine exhaust case is supported relative to a second shaft via at least a first support wall and a bearing.

Assignees

• United Technologies Corp

Inventors

• Roberge Gary D

Classifications

• F01D25/162

  Bearing supports · CPC title

• F05D2220/3213

  an intermediate stage of the turbine · CPC title

• F02C3/04 Primary

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

• F05D2260/40311

  of the epicyclical, planetary or differential type · CPC title

• F02K3/072

  with counter-rotating {, e.g. fan} rotors · CPC title