Turbine engine with a turbo-compressor

Patent metadata

Field	Value
Publication number	US-10100731-B2
Application number	US-201514622383-A
Country	US
Kind code	B2
Filing date	Feb 13, 2015
Priority date	Feb 13, 2015
Publication date	Oct 16, 2018
Grant date	Oct 16, 2018

Abstract

A turbine engine is provided that includes a first rotor, a second rotor and a combustor section. The first rotor includes a first set of compressor blades. The second rotor is adjacent the first rotor. The second rotor includes a second set of compressor blades and a set of turbine blades respectively connected to the second set of compressor blades. The combustor section is configured to receive air compressed by the first and the second sets of compressor blades. The combustor section is also configured to provide combustion products to the set of turbine blades.

First claim

What is claimed is:

1. A turbine engine, comprising:
a first rotor including a first set of compressor blades;
a second rotor adjacent the first rotor, the second rotor including a second set of compressor blades and a set of turbine blades, arranged radially outboard of the second set of compressor blades, wherein each turbine blade in the set of turbine blades is connected to a respective compressor blade in the second set of compressor blades; and
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.

2. The turbine engine of claim 1 , wherein the first rotor further includes a second set of turbine blades respectively connected to the first set of compressor blades.

3. The turbine engine of claim 2 , wherein the second set of turbine blades are downstream of 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 , further comprising a set of shrouds respectively positioned radially between and connected to the second set of compressor blades and the set of turbine blades.

6. The turbine engine of claim 1 , wherein the first rotor further includes a third set of compressor blades between the first set of compressor blades and the second set of compressor blades.

7. The turbine engine of claim 6 , wherein the third set of compressor blades respectively extend to blade tips.

8. The turbine engine of claim 6 , wherein the first rotor further includes a second set of turbine blades downstream of the set of turbine blades and respectively connected to the third set of compressor blades.

9. The turbine engine of claim 1 , wherein the second rotor further includes a third set of compressor blades.

10. The turbine engine of claim 9 , wherein the third set of compressor blades respectively extend to blade tips.

11. The turbine engine of claim 9 , wherein the second rotor further includes a second set of turbine blades respectively connected to the third set of compressor blades.

12. The turbine engine of claim 1 , further comprising a third rotor between the second set of compressor blades and the combustor section, wherein the third rotor includes a third set of compressor blades.

13. The turbine engine of claim 1 , further comprising a third rotor between the combustor section and the set of turbine blades, wherein the third rotor includes a second set of turbine blades.

14. The turbine engine of claim 1 , further comprising a fan section upstream of the first rotor.

15. The turbine engine of claim 14 , wherein a rotor of the fan section is connected to the first rotor.

16. The turbine engine of claim 14 , wherein a rotor of the fan section is connected to the second rotor.

17. The turbine engine of claim 14 , wherein a rotor of the fan section is connected to the first rotor and/or the second rotor through a gear train.

18. A turbine engine, comprising:
a first compressor section;
a turbo-compressor including a rotor disk, a second compressor section and a turbine section, the second compressor section comprising a set of compressor blades arranged circumferentially about the rotor disk, and the turbine section comprising a set of turbine blades arranged circumferentially about the set of compressor blades, wherein the second compressor section is downstream of the first compressor section; and
a combustor section fluidly coupled between the second compressor section and the turbine section.

19. The turbine engine of claim 18 , wherein the first compressor section includes a first rotor and the second compressor section comprises a second rotor which is discrete from the first rotor.

20. The turbine engine of claim 18 , wherein
the first compressor section includes a first set of compressor blades which respectively extend to blades tips;
the second compressor section includes a second set of compressor blades; and
the turbine section includes a set of turbine blades radially outboard of and respectively connected to the second set of compressor blades.

Assignees

• United Technologies Corp

Inventors

• Kupratis Daniel B
• Sheridan William G

Classifications

• F02C7/36

  Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user ({F02C3/107 - F02C3/13 and} F02C7/32 take precedence; couplings for transmitting rotation F16D; gearing in general F16H) · CPC title

• F05D2240/35

  Combustors or associated equipment · CPC title

• F01D1/12 Primary

  with repeated action on same blade ring · CPC title

• F02C3/045

  having compressor and turbine passages in a single rotor-module (F02C3/073 takes precedence) · CPC title

• F01D9/041

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