Reverse flow gas turbine engine core

• US 10,072,570 B2
• Filed: 01/28/2013
• Issued: 09/11/2018
• Est. Priority Date: 01/28/2013
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Kupratis, Daniel Bernard
• Primary Examiner(s): Wongwian, Phutthiwat
• Assistant Examiner(s): Edwards, Loren
• Application Number:
  US14/651,801
• Publication Number:
  US 20150322855A1
• Time in Patent Office: 2,052 Days
• Field of Search: 60805, 60262, 602261, 602263
• CPC Class Codes: F01D 1/04 traversed by the working-fluid substantially axially
• CPC Class Codes: F02C 3/06 the compressor comprising only axial stages F02C3/10 takes precedence
• CPC Class Codes: F02C 3/145 the combustion chamber being in the reverse flow-type
• CPC Class Codes: F02K 1/78 Other construction of jet pipes
• CPC Class Codes: F02K 3/075 controlling flow ratio between flows
• CPC Class Codes: F05D 2250/31 according to the direction of their main axis or their axis of rotation

Abstract

A gas turbine engine has a fan rotor for delivering air into a bypass duct and into a core airflow duct. Air in the core flow duct passes axially downstream from the fan and past a reverse core engine including a turbine section, a combustor section, and a compressor section. The core airflow duct reaches a turning duct which turns the airflow radially inwardly to communicate with an inlet for the compressor section. Air in the compressor section passes to the combustor section. Products of the combustion pass downstream across a turbine rotor. An exhaust turning duct communicates products of the combustion from a full cylindrical portion downstream of the turbine rotor through a plurality of circumferentially separated mixing lobe outlets to mix with the bypass air in the bypass duct. The bypass duct extends past the mixing lobe outlets, and is defined circumferentially intermediate the mixing lobe outlets.

Claims

1. A gas turbine engine comprising:

a fan rotor for delivering air into a bypass duct and into a core airflow duct, air in the core airflow duct passing axially downstream from the fan and past a reverse core engine including, serially, a turbine section, a combustor section, and a compressor section,

said core airflow duct reaching a turning duct which turns the airflow radially inwardly to communicate with an inlet for the compressor section, air in the compressor passing to the combustor section, and then products of the combustion passing downstream across a turbine rotor;

an exhaust turning duct for communicating products of the combustion from a downstream portion of the turbine rotor through a plurality of circumferentially separated mixing lobe outlets, to mix with the bypass air in the bypass duct, with the bypass duct having portions defined circumferentially intermediate the mixing lobe outlets; and

a door configured for selective opening to divert a portion of the air in the core airflow duct to an exhaust for the engine to provide additional propulsion.

2. The gas turbine engine as set forth in claim 1, wherein said mixing lobe outlets are connected to said downstream portion of said turning exhaust duct through vanes which communicate the products of combustion radially outwardly through said core airflow duct, which is radially inward of said bypass duct.

3. The gas turbine engine as set forth in claim 1, wherein said core airflow duct is radially outward of said bypass duct in an upstream location, and there being a change-over arrangement, whereby said core airflow duct is positioned radially inward of said bypass duct in a downstream location.

4. The gas turbine engine as set forth in claim 3, wherein said mixing lobe outlets mix the products of combustion with the bypass air upstream of the change-over arrangement.

5. The gas turbine engine as set forth in claim 1, wherein said turbine rotor drives a shaft which in turn drives said fan rotor.

6. The gas turbine engine as set forth in claim 1, wherein said downstream portion receives products of combustion over 360 degrees about a center axis of the engine.