Turbo-compressor with geared turbofan

Patent metadata

Field	Value
Publication number	US-9879694-B2
Application number	US-201514612614-A
Country	US
Kind code	B2
Filing date	Feb 3, 2015
Priority date	Feb 3, 2015
Publication date	Jan 30, 2018
Grant date	Jan 30, 2018

Abstract

A gas turbine engine includes a fan section. A turbo-compressor section is connected to the fan section through a speed change mechanism.

First claim

What is claimed is:

1. A gas turbine engine comprising:
a fan section;
a turbo-compressor section connected to the fan section through a speed change mechanism, wherein the turbo-compressor section includes at least one rotor stage having a plurality of blades with each of the plurality of blades having a low pressure compressor portion and a low pressure turbine portion; and
a high speed spool and a low speed spool, wherein the low speed spool connects the turbo-compressor section to the speed change mechanism and the high speed spool connects a high pressure compressor and a high pressure turbine.

2. The gas turbine engine of claim 1 , wherein the low pressure compressor portion is located radially inward from the low pressure turbine portion.

3. The gas turbine engine of claim 2 , further comprising a shroud separating the low pressure compressor portion and the low pressure turbine portion.

4. The gas turbine engine of claim 1 , wherein the low speed spool is spaced axially forward of the high speed spool.

5. The gas turbine engine of claim 1 , further comprising a mid-turbine passage having a first portion extending downstream from the high pressure turbine and a second portion extending upstream toward the turbo-compressor section.

6. The gas turbine engine of claim 5 , wherein the mid-turbine passage includes a plurality of ducts.

7. The gas turbine engine of claim 5 , wherein the mid-turbine passage includes a plenum.

8. The gas turbine engine of claim 5 , further comprising an exhaust passage fluidly connecting the turbo-compressor section to a bypass air duct.

9. A method of operating a gas turbine engine comprising:
rotating a turbo-compressor section including a plurality of turbo-compressor blades attached to a low speed spool, wherein each of the plurality of turbo-compressor blades have a low pressure compressor portion and a low pressure turbine portion; and
reducing a rotational output of the low speed spool with a speed change mechanism to rotate a fan section, wherein the low speed spool connects the turbo-compressor blades to the speed change mechanism and the high speed spool connects a high pressure compressor and a high pressure turbine.

10. The method of claim 9 , wherein the low pressure compressor portion is located radially inward from the low pressure turbine portion.

11. The method of claim 10 , further comprising a shroud separating the low pressure compressor portion and the low pressure turbine portion.

Assignees

• United Technologies Corp

Inventors

• Sheridan William G

Classifications

• F01D13/006

  one being a reverse turbine · CPC title

• F01D9/041

  using blades (F01D5/148 takes precedence) · CPC title

• F02C3/073

  the compressor and turbine stages being concentric · CPC title

• F02K3/04 Primary

  the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type · CPC title

• F01D25/162

  Bearing supports · CPC title