Turbine engine with a turbo-compressor

• US 10,125,722 B2
• Filed: 02/13/2015
• Issued: 11/13/2018
• Est. Priority Date: 02/13/2015
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Kupratis, Daniel B., Sheridan, William G.
• Primary Examiner(s): Manahan, Todd E
• Assistant Examiner(s): Diaz, Marcos O
• Application Number:
  US14/622,485
• Publication Number:
  US 20160356244A1
• Time in Patent Office: 1,369 Days
• CPC Class Codes: F01D 25/24 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 Class Codes: F01D 5/02 Blade-carrying members, e.g. rotors rotors of non-bladed type F01D1/34; stators F01D9/00 ; selecting particular materials F01D5/28
• CPC Class Codes: F02C 3/04 having a turbine driving a compressor power transmission arrangements F02C7/36; control of working fluid flow F02C9/16
• CPC Class Codes: F02C 3/045 having compressor and turbine passages in a single rotor-module F02C3/073 takes precedence
• CPC Class Codes: F02C 7/36 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 Class Codes: F02K 1/60 by blocking the rearward discharge by means of pivoted eyelids or clamshells, e.g. target-type reversers
• CPC Class Codes: F02K 1/68 Reversers mounted on the engine housing downstream of the fan exhaust section
• CPC Class Codes: F04D 19/002 Axial flow fans
• CPC Class Codes: F04D 29/321 for axial flow compressors
• CPC Class Codes: F04D 29/38 Blades for axial flow compressors F04D29/324
• CPC Class Codes: F04D 29/522 especially adapted for elastic fluid pumps
• CPC Class Codes: F05D 2220/32 in gas turbines
• CPC Class Codes: F05D 2240/20 Rotors
• CPC Class Codes: F05D 2260/40311 of the epicyclical, planetary or differential type

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.

Claims

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.