Turbine engine with single wall cantilevered architecture

Patent metadata

Field	Value
Publication number	US-10836499-B2
Application number	US-201715682834-A
Country	US
Kind code	B2
Filing date	Aug 22, 2017
Priority date	Aug 22, 2017
Publication date	Nov 17, 2020
Grant date	Nov 17, 2020

Abstract

An apparatus and method for mounting a turbine engine to an aircraft can include an engine core for the turbine engine including a compressor section, a combustor section, and a turbine section in flow arrangement. At least one strut couples to the engine core about a single mount plane. A structural wall at least partially defining a mainstream flow path couples to the at least one strut and passes through the compressor section and the turbine section.

First claim

What is claimed is:

1. A turbine engine comprising:
an engine core defining an engine centerline and including a compressor section, a combustor section, and a turbine section in sequential flow arrangement;
at least one mounting strut coupled to the engine core along a single mount plane between the compressor section and the turbine section; and
a structural wall supporting the engine core coupled to the at least one mounting strut and extending within at least the compressor section and the turbine section and forming a mainstream flow path at least partially through the compressor section and the turbine section, the structural wall including one or more openings permitting one or more structural sealing elements to extend from at least one of the compressor section or the turbine section into the mainstream flow path through the structural wall.

2. The turbine engine of claim 1 wherein the single mount plane has a width between 12 mm and 205 mm.

3. The turbine engine of claim 1 wherein the at least one mounting strut mounts to the engine core radially exterior of the combustor section.

4. The turbine engine of claim 1 further comprising at least one strut mount, coupling the at least one mounting strut to the structural wall.

5. The turbine engine of claim 4 further comprising at least one structural element coupling the at least one mounting strut to the structural wall along the compressor section and the turbine section.

6. The turbine engine of claim 1 wherein the one or more structural sealing elements include at least one of a blade, a seal, or a shroud.

7. The turbine engine of claim 1 wherein the engine core defines an engine centerline and the single mount plane is defined orthogonal to the engine centerline.

8. A turbine engine comprising:
an engine core having a compressor section and a turbine section, and including a mainstream flow path in sequential flow arrangement along the compressor section and the turbine section;
a mounting strut configured to mount the engine core to an aircraft along a single mount plane; and
a single structural wall at least partially forming the mainstream flow path and extending through the compressor section and the turbine section, the single structural wall including one or more openings permitting one or more structural sealing elements to extend from at least one of the compressor section or the turbine section into the mainstream flow path through the single structural wall.

9. The turbine engine of claim 8 further comprising a combustor section provided between the compressor section and the turbine section, wherein the mounting strut mounts within the combustor section.

10. The turbine engine of claim 9 wherein the one or more structural sealing elements include at least one of a blade, a seal, or a shroud.

11. The turbine engine of claim 8 further comprising an outer casing surrounding the engine core and the outer casing is supported by the structural wall.

12. A method of mounting a turbine engine defining an engine centerline to an aircraft, the method comprising:
supporting an engine core with at least one mounting strut about a single mount plane defined orthogonal to the engine centerline; and
supporting a single structural wall with the at least one mounting strut, with the single structural wall at least partially forming a mainstream flow path through the turbine engine, the single structural wall including one or more openings permitting one or more structural sealing elements to extend from the engine core into the mainstream flow path through the single structural wall.

13. The method of claim 12 further comprising mounting a casing to the single structural wall.

14. The method of claim 12 wherein the at least one mounting strut is configured to transfer loads from a propeller driven by the turbine engine to the aircraft.

15. The method of claim 12 wherein the turbine engine includes a turbine section and a compressor section, and the at least one mounting strut couples to the engine core between the turbine section and the compressor section.

16. The method of claim 15 wherein the single structural wall extends from the at least one mounting strut toward both the turbine section and the compressor section.

Assignees

• Gen Electric

Inventors

• Gould Kenneth Arthur
• D'Angelo Martin Miles
• Waslo Daniel
• Devendorf Brian Lewis
• Wotzak Mark Gregory

Classifications

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• B64D27/402

  comprising box like supporting frames, e.g. pylons or arrangements for embracing the power plant · CPC title

• B64D27/406

  Suspension arrangements specially adapted for supporting thrust loads, e.g. thrust links · CPC title

• B64D27/12 Primary

  within, or attached to, wings · CPC title

• F02C3/103

  the compressor being of the centrifugal type · CPC title