Turbine engine with a turbo-compressor

Patent metadata

Field	Value
Publication number	US-10041408-B2
Application number	US-201514622438-A
Country	US
Kind code	B2
Filing date	Feb 13, 2015
Priority date	Feb 13, 2015
Publication date	Aug 7, 2018
Grant date	Aug 7, 2018

Abstract

A turbine engine is provided that includes a turbo-compressor and a combustor section. The turbo-compressor includes a compressor section and a turbine section. The combustor section is fluidly coupled between the compressor section and the turbine section. The compressor section includes a first number of stages. The turbine section includes a second number of stages that is different than the first number.

First claim

What is claimed is:

1. A turbine engine, comprising:
a turbo-compressor including a compressor section and a turbine section, wherein the compressor section includes a first set of compressor blades and a second set of compressor blades axially offset from the first set of compressor blades with respect to an axial centerline of the turbine engine, and the turbine section includes a set of turbine blades radially outboard of and respectively connected to the second set of compressor blades via a blade shroud directly connecting a radially outward portion of each compressor blade of the second set of compressor blades with a radially inward portion of a corresponding turbine blade of the set of turbine blades;
a combustor section fluidly coupled between the compressor section and the turbine section;
a fan section upstream of the turbo-compressor;
a second compressor section comprising a compressor rotor; a second turbine section comprising a turbine rotor; and a shaft, wherein the compressor rotor is connected to and driven by the turbine rotor through the shaft;
wherein the compressor section includes a first number of stages and the turbine section includes a second number of stages that is different than the first number,
and wherein the second compressor section is axially aft of the turbo-compressor, and axially forward of the second turbine section.

2. The turbine engine of claim 1 , wherein the first number is greater than the second number.

3. The turbine engine of claim 1 , wherein the turbo-compressor includes a set of shrouds comprising each blade shroud respectively positioned between the second set of compressor blades and the set of turbine blades.

4. The turbine engine of claim 1 , wherein the first set of compressor blades respectively extend to blade tips.

5. The turbine engine of claim 1 , wherein the first set of compressor blades are upstream of the second set of compressor blades.

6. The turbine engine of claim 1 , wherein the first set of compressor blades are downstream of the second set of compressor blades.

7. The turbine engine of claim 1 , wherein the turbo-compressor includes a rotor which includes the first set of compressor blades, the second set of compressor blades and the set of turbine blades.

8. The turbine engine of claim 1 , further comprising the second compressor section fluidly coupled between the compressor section and the combustor section.

9. The turbine engine of claim 1 , further comprising the second turbine section fluidly coupled between the combustor section and the turbine section.

10. The turbine engine of claim 1 , wherein a rotor of the fan section is connected to a rotor of the turbo-compressor.

11. The turbine engine of claim 1 , wherein a rotor of the fan section is connected to a gear train.

12. A turbine engine, comprising:
a turbo-compressor including a first set of compressor blades, a second set of compressor blades axially offset from the first set of compressor blades with respect to an axial centerline of the turbine engine, and a set of turbine blades radially outboard of and respectively connected to the second set of compressor blades via a blade shroud directly connecting a radially outward portion of each compressor blade of the second set of compressor blades with a radially inward portion of a corresponding turbine blade of the set of turbine blades;
a combustor section configured to receive air compressed by the first and the second sets of compressor blades and provide combustion products to the set of turbine blades;
a fan section upstream of the turbo-compressor; wherein the first set of compressor blades respectively extend to blade tips; and
a compressor section comprising a compressor rotor; a turbine section comprising a turbine rotor; and a shaft, the compressor rotor connected to and driven by the turbine rotor through the shaft;
wherein the first set of compressor blades respectively extend to blade tips, and
wherein the compressor section is axially aft of the turbo-compressor, and axially forward of the turbine section.

13. The turbine engine of claim 12 , wherein the turbo-compressor includes a set of shrouds comprising each blade shroud respectively positioned between the second set of compressor blades and the set of turbine blades.

14. The turbine engine of claim 12 , wherein the first set of compressor blades are upstream of the second set of compressor blades.

15. The turbine engine of claim 12 , wherein the turbo-compressor includes a rotor which includes the first set of compressor blades, the second set of compressor blades and the set of turbine blades.

16. A turbine engine, comprising:
a turbo-compressor including a compressor section and a turbine section, the compressor section including a first set of compressor blades and a second set of compressor blades axially offset from the first set of compressor blades with respect to an axial centerline of the turbine engine, and the turbine section including a set of turbine blades radially outboard of and respectively connected to the second set of compressor blades via a blade shroud directly connecting a radially outward portion of each compressor blade of the second set of compressor blades with a radially inward portion of a corresponding turbine blade of the set of turbine blades;
a combustor section configured to receive air compressed by the first and the second sets of compressor blades and provide combustion products to the set of turbine blades;
a second compressor section comprising a compressor rotor; a second turbine section comprising a turbine rotor; and a shaft, the compressor rotor connected to and driven by the turbine rotor through the shaft;
wherein the first set of compressor blades respectively extend to blade tips, and
wherein the second compressor section is axially aft of the turbo-compressor, and axially forward of the second turbine section.

Assignees

• United Technologies Corp

Inventors

• Kupratis Daniel B
• Sheridan William G

Classifications

• F01D13/006

  one being a reverse turbine · CPC title

• F02C3/06

  the compressor comprising only axial stages (F02C3/10 takes precedence) · CPC title

• F05D2250/36

  in inner-outer relationship, e.g. shaft-bearing arrangements · CPC title

• F02C3/073

  the compressor and turbine stages being concentric · CPC title

• F01D5/02

  Blade-carrying members, e.g. rotors (rotors of non-bladed type F01D1/34; stators F01D9/00 {; selecting particular materials F01D5/28}) · CPC title