INLET FLOW STRUCTURE FOR TURBOPROP ENGINE

• US 20200130857A1
• Filed: 10/25/2018
• Published: 04/30/2020
• Est. Priority Date: 10/25/2018
• Status: Active Grant

• Current Assignee: Honeywell International Inc.
• Original Assignee: Honeywell International Inc.
• Inventors: Mccage, Raymond, Rice, Derek Anthony, Becar, Joseph, Wong, Yates, Jardine, Brian, Bouldin, Bruce Dan, Sing, Kevin
• Granted Patent: US 11,072,435 B2
• Time in Patent Office: Days
• CPC Class Codes: B64D 2033/0293 for turboprop engines
• CPC Class Codes: B64D 27/10 of gas-turbine type jet aircraft B64D27/16
• CPC Class Codes: B64D 33/02 of combustion air intakes air intakes for gas-turbine plants or jet-propulsion plants per se F02C7/04; air intakes for combustion engines in general F02M35/00
• CPC Class Codes: B64D 35/02 specially adapted for specific power plants
• CPC Class Codes: F02C 6/206 the vehicles being airscrew driven
• CPC Class Codes: F02C 7/04 Air intakes for gas-turbine plants or jet-propulsion plants
• CPC Class Codes: F02C 7/047 Heating to prevent icing
• CPC Class Codes: F02C 7/20 Mounting or supporting of plant; Accommodating heat expansion or creep
• CPC Class Codes: F02C 7/36 Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user F02C3/107 - F02C3/13 and F02C7/32 take precedence; couplings for transmitting rotation F16D; gearing in general F16H
• CPC Class Codes: F05D 2220/323 for aircraft propulsion, e.g. jet engines
• CPC Class Codes: F05D 2220/324 to drive unshrouded, low solidity propeller
• CPC Class Codes: F05D 2230/642 using maintaining alignment while permitting differential dilatation
• CPC Class Codes: F05D 2250/51 Inlet
• CPC Class Codes: F05D 2250/75 given by its similarity to a letter, e.g. T-shaped
• CPC Class Codes: F05D 2260/31 Retaining bolts or nuts

Abstract

A turboprop engine system for an aircraft includes an engine, a propeller, and a gear train coupled to and configured to provide power from the engine to the propeller at a predetermined gear reduction. The engine system also includes a gearbox that houses at least part of the gear train. The gearbox includes a gearbox flow structure and an inlet flow structure that is removably attached to the gearbox. The inlet flow structure and the gearbox flow structure cooperate to define an inlet flow passage to the engine. The inlet flow passage has an upstream end and a downstream end that are cooperatively defined by the inlet flow structure and the gearbox flow structure. The upstream end is configured to receive an airstream that is directed along the inlet flow passage to the downstream end and toward the engine.

Claims

1. A turboprop engine system for an aircraft comprising:

an engine;

a propeller;

a geartrain coupled to and configured to provide power from the engine to the propeller at a predetermined gear reduction;

a gearbox that houses at least part of the geartrain, the gearbox including a gearbox flow structure; and

an inlet flow structure that is removably attached to the gearbox, the inlet flow structure and the gearbox flow structure cooperating to define an inlet flow passage to the engine, the inlet flow passage having an upstream end and a downstream end that are cooperatively defined by the inlet flow structure and the gearbox flow structure, the upstream end configured to receive an airstream that is directed along the inlet flow passage to the downstream end and toward the engine.

2. The turboprop engine system of claim 1, wherein the inlet flow structure includes an edge that extends in a longitudinal direction from the upstream end to the downstream end;

and

wherein the inlet flow structure is removably attached to the gearbox at the edge.

3. The turboprop engine system of claim 1, wherein the inlet flow passage extends along a longitudinal axis of the engine system;

wherein the upstream end is arcuate and discontinuous about the axis; and

wherein the downstream end is annular and continuous about the axis.

4. The turboprop engine system of claim 1, wherein the gearbox includes a support arm that extends at least partially about the inlet flow structure;

and

wherein the inlet flow structure is attached to the support arm.

5. The turboprop engine system of claim 4, wherein the gearbox flow structure and the support arm cooperate to continuously surround the inlet flow structure.

6. The turboprop engine system of claim 4, further comprising an outer support structure that attaches the engine to the gearbox;

and

wherein the outer support structure is attached to the support arm.

7. The turboprop engine system of claim 4, wherein the support arm and the inlet flow structure are fixedly attached together at a fixed joint;

and

further comprising at least one moveable joint that supports the inlet flow structure on the turboprop engine system.

8. The turboprop engine system of claim 7, wherein the inlet flow passage extends along a flow axis;

wherein the fixed joint is disposed between the upstream end and the downstream end with respect to the flow axis.

9. The turboprop engine system of claim 8, wherein the engine includes a rotating group that is supported for rotation about an axis;

wherein the fixed joint is disposed substantially within a first plane;

wherein the upstream end is disposed substantially within a second plane;

wherein the downstream end is disposed substantially within a third plane;

wherein the first plane is disposed at an angle relative to the axis of rotation; and

wherein the second plane and the third plane are substantially normal to the axis of rotation.

10. The turboprop engine system of claim 7, wherein the inlet flow structure includes an edge that extends in a longitudinal direction from the upstream end to the downstream end;

wherein the inlet flow structure is removably attached to the gearbox at the edge; and

wherein the at least one moveable joint includes a first moveable joint at the edge.

11. The turboprop engine system of claim 7, further comprising a first outer support structure that supports the gearbox and the inlet flow structure at the upstream end;

wherein the at least one moveable joint includes a second moveable joint between the first outer support structure and the inlet flow structure.

12. The turboprop engine system of claim 7, further comprising an impeller and a compressor shroud that are disposed proximate the downstream end;

and

wherein the at least one moveable joint includes a third moveable joint between the downstream end and the compressor shroud.

13. The turboprop engine system of claim 1, wherein the inlet flow structure includes a first wall, a second wall, and an internal flow passage that is defined between the first wall and the second wall, the internal flow passage configured to receive a de-icing fluid flow.

14. The turboprop engine system of claim 13, further comprising a partition that extends between the first wall and the second wall;

and

wherein the partition separates the internal flow passage into a first flowpath and a second flowpath.

15. The turboprop engine system of claim 13, wherein the internal flow passage includes an inlet and an outlet;

wherein the internal flow passage extends through the inlet flow structure, from the inlet in an aftward direction and turns forward toward the outlet.

16. The turboprop engine system of claim 1, wherein the engine includes a rotating group that is supported for rotation about a first axis;

wherein the propeller is supported for rotation about a second axis;

wherein the first axis and the second axis are substantially parallel and spaced apart at a distance.

17. A method of manufacturing a turboprop engine system comprising:

removably attaching an inlet flow structure to a gearbox, the gearbox configured to house at least part of a geartrain that provides power from an engine to a propeller at a predetermined gear reduction, the gearbox including a gearbox flow structure; and

the inlet flow structure and the gearbox flow structure, when removably attached, cooperating to define an inlet flow passage to the engine, the inlet flow passage having an upstream end and a downstream end that are cooperatively defined by the inlet flow structure and the gearbox flow structure, the upstream end configured to receive an airstream that is directed along the inlet flow passage to the downstream end and toward the engine.

18. The method of claim 17, wherein removably attaching the inlet flow structure to the gearbox includes:

attaching the inlet flow structure to the gearbox at a first joint that is substantially fixed; and

attaching the inlet flow structure to the gearbox at a second joint that is moveable.

19. The method of claim 17, further comprising attaching the inlet flow structure and the gearbox to another structure at a third joint;

and

wherein the third joint is moveable.

20. A turboprop engine system for an aircraft comprising:

an engine with a compressor shroud;

a propeller;

a gear train coupled to and configured to provide power from the engine to the propeller at a predetermined gear reduction;

a gearbox that houses at least part of the gear train, the gearbox including a gearbox flow structure; and

an inlet flow structure that is removably attached to the gearbox to cooperatively define an intake system with an inlet flow passage to the engine, the inlet flow passage having an upstream end and a downstream end that are cooperatively defined by the inlet flow structure and the gearbox flow structure, the upstream end configured to receive an airstream that is directed along the inlet flow passage to the downstream end and toward the engine;

the inlet flow structure and the gearbox removably attached at a first joint that is a fixed joint;

the inlet flow structure and the gearbox removably attached at a second joint that is a moveable joint; and

the intake system attached to the compressor shroud proximate the downstream end at a third joint, the third joint being a moveable joint.