Tip turbine engine support structure

• US 7,976,273 B2
• Filed: 12/01/2004
• Issued: 07/12/2011
• Est. Priority Date: 12/01/2004
• Status: Expired due to Fees

• Current Assignee: United Technologies Corporation (Rtx Corporation)
• Original Assignee: United Technologies Corporation (Rtx Corporation)
• Inventors: Suciu, Gabriel L., Merry, Brian
• Primary Examiner(s): Look; Edward
• Assistant Examiner(s): White; Dwayne J
• Application Number:
  US11/720,536
• Publication Number:
  US 20080095618A1
• Time in Patent Office: 2,414 Days
• Field of Search: 415/182.1, 415/209.2, 415/220, 415/199.5, 415/162, 415/211.2, 60/394.3, 602/68, 60/391.62, 602/261
• US Class Current: 415/182.1
• CPC Class Codes: F01D 25/28 Supporting or mounting arrangements, e.g. for turbine casing
• CPC Class Codes: F01D 5/022 with concentric rows of axial blades
• CPC Class Codes: F02C 3/073 the compressor and turbine stages being concentric
• CPC Class Codes: F02C 7/20 Mounting or supporting of plant; Accommodating heat expansion or creep
• CPC Class Codes: F02K 3/068 being characterised by a short axial length relative to the diameter

Abstract

A tip turbine engine assembly according to the present invention includes a load bearing engine support structure (12). The engine support structure (12) includes an engine support plane (P) that is substantially perpendicular to an engine centerline (A) and first rotationally fixed member (50) disposed about the engine centerline (A) and cantilevered from the engine support plane (P). A support member extends radially outward from the first rotationally fixed member (50) and structurally supports a second rotationally fixed member (58) that is coaxial with the first rotationally fixed member. A rotor is mounted on the first rotationally fixed member and rotates about the engine centerline (A).

Claims

1. A tip turbine engine assembly comprising:

a first rotationally fixed member disposed about an engine centerline;

a support member extending radially from said first rotationally fixed member;

a second rotationally fixed member attached to said support member and disposed coaxially with said first rotationally fixed member;

a rotor mounted between said first rotationally fixed member and said second rotationally fixed member, said rotor comprising compressor blades that extend radially outward;

a guide vane extending radially outwards from the second rotationally fixed member; and

a housing disposed radially outward of the first rotationally fixed member, wherein the housing is attached to both the first rotationally fixed member and the guide vane.

2. The assembly as recited in claim 1, wherein said first rotationally fixed member and said second rotationally fixed member define a flow path therebetween.

3. The assembly as recited in claim 2, wherein said rotor is rotatable in said flow path.

4. The assembly as recited in claim 1, wherein said first rotationally fixed member comprises a static cylindrical shaft.

5. The assembly as recited in claim 1, wherein said second rotationally fixed member comprises a compressor case with compressor vanes that extend radially inward.

6. The assembly as recited in claim 5, wherein the case is disposed radially outwards of the first rotationally fixed member, wherein the guide vane extends between the first rotationally fixed member and the case and is attached to both the first rotationally fixed member and the case.

7. The assembly as recited in claim 1, further comprising a gearbox assembly aft of the support member.

8. A tip turbine engine assembly comprising:

a plurality of fan blades fixed to a fan rotor rotatable about an engine centerline, each of said plurality of fan blades defining a core airflow passage therethrough;

a first rotationally fixed member disposed coaxially with said engine centerline;

a support member extending radially from said first rotationally fixed member;

a second rotationally fixed member fixed to said support member and disposed coaxially with said first rotationally fixed member;

a compressor rotor mounted on said first rotationally fixed member for rotation about said engine centerline, wherein a guide vane extends radially outwards from the second rotationally fixed member.

9. The assembly as recited in claim 8, wherein said compressor rotor and said fan rotor are distinct from one another.

10. The assembly as recited in claim 8, wherein said compressor rotor and said fan rotor rotate at different speeds.

11. The assembly as recited in claim 8, wherein said first rotationally fixed member comprises a cylindrical shaft.

12. The assembly as recited in claim 8, wherein second rotationally fixed member comprises a compressor case with compressor vanes that extend radially inward.

13. The assembly as recited in claim 8, wherein said compressor rotor comprises compressor blades that extend radially outward.

14. The assembly as recited in claim 8, wherein a case is disposed radially outward of the second rotationally fixed member, wherein the guide vane is attached to the case and the second rotationally fixed member.

15. The assembly as recited in claim 8, further comprising a gearbox assembly aft of the plurality of fan blades.

16. The assembly of claim 8, further comprising a housing disposed radially outward of the first rotationally fixed member, wherein the housing is attached to both the first rotationally fixed member and the guide vane.