Gas turbine engine with aft core driven fan section

• US 8,516,789 B2
• Filed: 07/26/2011
• Issued: 08/27/2013
• Est. Priority Date: 07/26/2011
• Status: Expired due to Fees

• Current Assignee: Raytheon Technologies Corporation d/b/a RTX (Rtx Corporation)
• Original Assignee: United Technologies Corporation (Rtx Corporation)
• Inventors: Kupratis, Daniel B.
• Primary Examiner(s): NGUYEN, ANDREW H
• Application Number:
  US13/190,595
• Publication Number:
  US 20130025286A1
• Time in Patent Office: 763 Days
• Field of Search: 602261-2263, 602/62, 60/391.5, 60791-792, 602/24, 60/394.2, 608/05
• US Class Current: 60/226.1
• CPC Class Codes: F02C 3/13 having variable working fluid interconnections between turbines or compressors or stages of different rotors controlling flow ratio between different flows of multi-flow jet-propulsion plant, e.g. ducted fan F02K3/075
• CPC Class Codes: F02C 3/145 the combustion chamber being in the reverse flow-type
• CPC Class Codes: F02K 3/065 with front and aft fans
• CPC Class Codes: F02K 3/075 controlling flow ratio between flows
• CPC Class Codes: F02K 3/077 the plant being of the multiple flow type, i.e. having three or more flows

Abstract

A gas turbine engine includes a low spool along an engine axis with a forward fan section and a low pressure turbine section. A high spool along the engine axis with a high pressure turbine section and an aft core driven fan section (CDFS), the aft core driven fan section (CDFS) axially aft of the high pressure turbine section along the engine axis.

Claims

1. A gas turbine engine comprising:

a low spool along an engine axis with a forward fan section and a low pressure turbine section;

a high spool along said engine axis with a high pressure turbine section, a high pressure compressor section and an aft core driven fan section (CDFS), said high pressure turbine section axially forward of said high pressure compressor section, said aft core driven fan section (CDFS) axially aft of said high pressure turbine section and said high pressure compressor section along said engine axis, and said aft core driven fan section (CDFS) including a forward-facing inlet; and

a combustor section axially between said high pressure turbine section and said high pressure compressor section.

2. The gas turbine engine as recited in claim 1, wherein said forward fan section includes a multiple of stages.

3. The gas turbine engine as recited in claim 1, wherein said low pressure turbine section is axially aft of said forward fan section.

4. The gas turbine engine as recited in claim 1, further comprising a Fan Exit Guide Vane (FEGV) structure located axially between said forward fan section and said low pressure turbine section.

5. The gas turbine engine as recited in claim 4, wherein said Fan Exit Guide Vane (FEGV) structure mixes a combustion gas core flow from said high pressure turbine section with a fan air from an outer diameter of said forward fan section.

6. The gas turbine engine as recited in claim 5, further comprising a third stream flow primarily sourced from an inner diameter of said forward fan section.

8. The gas turbine engine as recited in claim 1, wherein said aft core driven fan section (CDFS) is radially between an inner case structure and a third stream case structure which form a third stream exhaust duct.

9. The gas turbine engine as recited in claim 8, wherein said third stream exhaust duct is radially inward of a mixed flow exhaust duct.

13. The gas turbine engine as recited in claim 1, wherein said aft core driven fan section (CDFS) includes a vane and a rotor, said vane being adjustable between open and closed positions, said closed position diverting a third stream exhaust to an inlet of said high pressure compressor section.

14. The gas turbine engine as recited in claim 1, wherein said forward fan section is in communication with a third stream flow path, a third stream exhaust duct, and a mixed flow exhaust duct, said high pressure turbine section being arranged to discharge into said mixed flow exhaust duct.

15. The gas turbine engine as recited in claim 14, wherein said high pressure compressor section is arranged in receiving flow communication with said third stream flow path.

16. The gas turbine engine as recited in claim 14, wherein said aft core driven fan section (CDFS) is in exclusive flow communication with said third stream exhaust duct.

17. The gas turbine engine as recited in claim 14, wherein said third stream exhaust duct is radially inwards of said mixed flow exhaust duct.

7. A gas turbine engine comprising:

a low spool along an engine axis with a forward fan section and a low pressure turbine section;

a high spool along said engine axis with a high pressure turbine section and an aft core driven fan section (CDFS), said aft core driven fan section (CDFS) axially aft of said high pressure turbine section along said engine axis;

a Fan Exit Guide Vane (FEGV) structure located axially between said forward fan section and said low pressure turbine section, said Fan Exit Guide Vane (FEGV) structure mixes a combustion gas core flow from said high pressure turbine section with a fan air from an outer diameter of said forward fan section; and

a third stream flow primarily sourced from an inner diameter of said forward fan section, wherein said third stream flow is split between said aft core driven fan section (CDFS) and a high pressure compressor axially forward of said aft core driven fan section (CDFS).

10. A gas turbine engine comprising:

a forward fan section in communication with a third stream flow path, a third stream exhaust duct, and a mixed flow exhaust duct;

a compressor section arranged in receiving flow communication with said third stream flow path;

a combustor section arranged in receiving flow communication with said third stream flow path;

a turbine section arranged in receiving flow communication with said combustor section and located forward of said compressor section;

an aft core driven fan section (CDFS) axially aft of said compressor section, said aft core driven fan section (CDFS) in communication with said third stream exhaust duct, and said aft core driven fan section (CDFS) including an inlet guide vane and a rotor, said vane being adjustable between open and closed positions, said closed position configured to divert flow from said third stream exhaust duct to an inlet of said compressor section.

11. The gas turbine engine as recited in claim 10, wherein said aft core driven fan section (CDFS) includes the inlet guide vane radially between an inner case structure and a third stream case structure which forms said third stream exhaust duct.

12. The gas turbine engine as recited in claim 10, wherein said mixed flow exhaust duct is radially outward of said third stream exhaust duct.