Turbine engine with a turbo-compressor

Patent metadata

Field	Value
Publication number	US-10125722-B2
Application number	US-201514622485-A
Country	US
Kind code	B2
Filing date	Feb 13, 2015
Priority date	Feb 13, 2015
Publication date	Nov 13, 2018
Grant date	Nov 13, 2018

Abstract

A turbine engine is provided that include a turbo-compressor, a combustor section and a nacelle which houses the turbo-compressor and the 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 nacelle includes a thrust reverser.

First claim

What is claimed is:

1. A turbine engine, comprising:
a turbo-compressor including a compressor section and a turbine section, wherein the turbo-compressor includes a rotor with a plurality of compressor blades and a plurality of turbine blades radially outboard of and respectively connected to the compressor blades;
a fan section upstream of the turbo-compressor;
a combustor section fluidly coupled between the compressor section and the turbine section;
a second compressor section fluidly coupled between the compressor section and the combustor section, the second compressor section comprising a compressor rotor
a second turbine section fluidly coupled between the combustor section and the turbine section, the second turbine section comprising a turbine rotor that is connected to the compressor rotor through a shaft; and
a nacelle housing the turbo-compressor and the combustor section, wherein the nacelle includes a thrust reverser;
wherein the turbo-compressor is axially between the fan section and the combustor section along an axial centerline of the turbine engine.

2. The turbine engine of claim 1 , further comprising a second nacelle housing the fan section and axially overlapping the nacelle.

3. The turbine engine of claim 1 , wherein the thrust reverser comprises a clamshell thrust reverser.

4. The turbine engine of claim 1 , wherein the thrust reverser includes at least one panel configured to pivot outward from a stowed position to a deployed position.

5. The turbine engine of claim 4 , wherein the nacelle includes a stationary structure, and an aft end of the panel is pivotally connected to the stationary structure.

6. The turbine engine of claim 4 , wherein the panel is at a top portion of the nacelle.

7. The turbine engine of claim 4 , wherein the panel is at a bottom portion of the nacelle.

8. The turbine engine of claim 1 , wherein the thrust reverser includes a pair of panels arranged at opposing portions of the nacelle, and the panels are configured to move between a stowed position and a deployed position.

9. The turbine engine of claim 8 , wherein the opposing portions of the nacelle comprise a top portion of the nacelle and a bottom portion of the nacelle.

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 compressor section and a turbine section, wherein the turbo-compressor includes a rotor with a plurality of compressor blades and a plurality of turbine blades radially outboard of and respectively connected to the compressor blades, the rotor rotatable about an axial centerline;
a fan section upstream of the turbo-compressor;
a combustor section fluidly coupled between the compressor section and the turbine section, wherein the turbo-compressor is axially between the fan section and the combustor section along the axial centerline; and
a nacelle housing the turbo-compressor and the combustor section, wherein the nacelle forms an inner wall of a bypass flow path and includes a clamshell thrust reverser.

13. The turbine engine of claim 12 , wherein the thrust reverser includes a pair of panels arranged at opposing portions of the nacelle, and the panels are configured to move between a stowed position and a deployed position.

14. The turbine engine of claim 13 , wherein the opposing portions of the nacelle comprise a top portion of the nacelle and a bottom portion of the nacelle.

15. A turbofan turbine engine with an axial centerline, comprising:
a turbine engine core comprising a turbo-compressor and a combustor, wherein the turbo-compressor includes a rotor with a plurality of compressor blades and a plurality of turbine blades radially outboard of and respectively connected to the compressor blades;
a fan section upstream of the turbine engine core and comprising a fan rotor, wherein the rotor is axially between the fan rotor and the combustor along the axial centerline;
a core nacelle housing the turbine engine core and comprising a thrust reverser; and
a fan nacelle housing the fan section and axially overlapping the core nacelle, wherein a bypass flow path is formed between the core nacelle and the fan nacelle;
wherein the combustor is fluidly coupled between the compressor blades and the turbine blades.

16. The turbine engine of claim 15 , wherein the thrust reverser includes a pair of panels arranged at opposing top and bottom portions of the nacelle, and the panels are configured to move between a stowed position and a deployed position.

Assignees

• United Technologies Corp

Inventors

• Kupratis Daniel B
• Sheridan William G

Classifications

• F01D25/24

  Casings (modified for heating or cooling F01D25/14); Casing parts, e.g. diaphragms, casing fastenings (casings for rotary machines or engines in general F16M {; special arrangements in stators dealing with breaking-off of part of rotor F01D21/045}) · CPC title

• F04D29/522

  especially adapted for elastic fluid pumps · CPC title

• F04D29/38

  Blades {(for axial flow compressors F04D29/324)} · CPC title

• F02C3/045

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

• F04D29/321

  for axial flow compressors · CPC title