Turbine engine with a turbo-compressor

Patent metadata

Field	Value
Publication number	US-2016356244-A1
Application number	US-201514622485-A
Country	US
Kind code	A1
Filing date	Feb 13, 2015
Priority date	Feb 13, 2015
Publication date	Dec 8, 2016
Grant date	—

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; a combustor section fluidly coupled between the compressor section and the turbine section; and a nacelle housing the turbo-compressor and the combustor section, wherein the nacelle includes a thrust reverser.

2 . The turbine engine of claim 1 , further comprising:
a fan section upstream of the turbo-compressor; and 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 gravitational top portion of the nacelle.

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

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

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

12 . The turbine engine of claim 1 , further comprising a fan section upstream of the turbo-compressor.

13 . The turbine engine of claim 12 , wherein a rotor of the fan section is connected to a rotor of the turbo-compressor.

14 . The turbine engine of claim 12 , wherein a rotor of the fan section is connected to a gear train.

15 . The turbine engine of claim 1 , 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.

16 . A turbine engine, comprising:
a turbo-compressor including a compressor section and a turbine section; a combustor section fluidly coupled between the compressor section and the turbine section; 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.

17 . The turbine engine of claim 16 , 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.

18 . The turbine engine of claim 17 , wherein the opposing portions of the nacelle comprise a gravitational top portion of the nacelle and a gravitational bottom portion of the nacelle.

19 . A turbofan turbine engine, comprising:
a turbine engine core comprising a turbo-compressor; a fan section upstream of the turbine engine core; 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.

20 . The turbine engine of claim 19 , 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

• F02C3/04

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

• F02K1/60 Primary

  by blocking the rearward discharge by means of pivoted eyelids or clamshells, e.g. target-type reversers · CPC title

• 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

• 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

• F05D2240/20

  Rotors · CPC title