Cantilevered tip turbine engine

• US 8,033,094 B2
• Filed: 12/01/2004
• Issued: 10/11/2011
• Est. Priority Date: 12/01/2004
• Status: Expired due to Fees

• Current Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Roberge, Gary D., Suciu, Gabriel L., Merry, Brian
• Primary Examiner(s): Casaregola; Louis
• Assistant Examiner(s): Wongwian; Phutthiwat
• Application Number:
  US11/577,595
• Publication Number:
  US 20080087023A1
• Time in Patent Office: 2,505 Days
• Field of Search: 602/261, 602/62, 60796-797, 608/05, 415/68, 416/124
• US Class Current: 60/226.1
• 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 7/06 Arrangements of bearings bearings F16C; Lubricating of turbo machines F01D25/18; of machines or engines in general F01M
• 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 (10) according to the present invention includes an engine support structure (12) for cantilevering a load bearing shaft from an engine support plane (P). An engine support structure (12) defines the engine support plane (P), which is perpendicular to an engine centerline (A). The shaft (60) is rotationally fixed, coaxial with the engine centerline (A), and structurally supported by the engine support structure (12) such that a load borne by the shaft (60) is transferred along the engine support plane.

Claims

1. A tip turbine engine assembly comprising:

an axial compressor having a plurality of compressor blades;

a fan downstream of the axial compressor;

an engine support plane defined by an engine support structure;

an engine centerline axis essentially perpendicular to said support plane; and

a fixed shaft coaxial with said engine centerline axis, the fixed shaft having a forward end aft of the plurality compressor blades, said fixed shaft being non-moveable during operation, wherein said fixed shaft is cantilevered from said engine support plane by the engine support structure.

2. The assembly as recited in claim 1, wherein said engine support plane is the sole engine support plane of the tip turbine engine assembly.

3. The assembly as recited in claim 1, further comprising a fan having a fan blade defining a core airflow passage therethrough, wherein said engine support plane is aft of said fan.

4. The assembly as recited in claim 1, further comprising a rotor coaxial with said fixed shaft.

5. The assembly as recited in claim 4, wherein said rotor comprises an axial compressor rotor that rotates about said fixed shaft.

6. The assembly as recited in claim 1, wherein the engine support structure is a plurality of guide vanes that extend radially relative to said engine centerline define said engine support plane.

7. The assembly of claim 1, further comprising an axial compressor and a bypass fan coaxially mounted about the engine centerline axis, wherein the bypass fan is aft of the axial compressor.

8. The assembly of claim 7, wherein the bypass fan includes hollow fan blades.

9. A tip turbine engine assembly comprising:

an engine centerline;

a fan rotatable by a gear assembly about said engine centerline, said fan comprising a fan blade defining a core airflow passage therein;

an engine support structure disposed about said engine centerline defining an engine support plane substantially perpendicular to said engine centerline; and

a shaft coaxial with said engine centerline and fixed to said engine support structure such that the shaft is non-moveable during operation of the engine, wherein said shaft is cantilevered from said engine support plane.

10. The assembly as recited in claim 9, wherein said engine support plane is the sole engine support plane of the assembly.

11. The assembly as recited in claim 9, wherein said shaft is fixed.

12. The assembly as recited in claim 9, wherein said engine support structure comprises an engine outer case with a guide vane portion extending radially inward from said engine outer case, said guide vane portion structurally supporting said shaft.

13. The assembly of claim 12, wherein the guide vane portion is formed integrally with the engine outer case.

14. The assembly as recited in claim 9, wherein said engine support structure comprises a plurality of engine mounts attached on a periphery of an outer case in said engine support plane.

15. The assembly as recited in claim 9, wherein said shaft supports a rotor rotatable about said engine centerline.

16. The assembly as recited in claim 15, further comprising a bearing between said shaft and said rotor.

17. A tip turbine engine assembly comprising:

an engine centerline;

an engine outer case structure disposed about said engine centerline;

a guide vane portion that extends radially inward from said engine outer case structure;

a gearbox housing fixed to said guide vane portion, the gearbox housing enclosing a gear assembly that rotates with an axial compressor; and

a shaft coaxial with said engine centerline and fixed to said gearbox housing such that the shaft is non-moveable during operation, wherein said shaft is cantilevered from said gearbox.

18. The assembly as recited in claim 17, wherein said engine outer case structure comprises a plurality of engine mounts defining an engine support plane.

19. The assembly of claim 18, further comprising a fan turbine rotor assembly about the engine centerline axis, wherein the plurality of engine mounts are axially aft of the fan turbine rotor assembly.

20. The assembly as recited in claim 17, further comprising a rotor supported by said shaft.

21. The assembly as recited in claim 20, further comprising a bearing between said rotor and said shaft.