Airplane with angled-mounted turboprop engine

Patent metadata

Field	Value
Publication number	US-10507930-B2
Application number	US-201615359188-A
Country	US
Kind code	B2
Filing date	Nov 22, 2016
Priority date	Nov 22, 2016
Publication date	Dec 17, 2019
Grant date	Dec 17, 2019

Abstract

An airplane including an airframe and a turboprop propulsion system is disclosed in this paper. The turboprop propulsion system includes a propeller mounted for rotation about a propeller axis and a gas turbine coupled to the propeller to drive rotation of the propeller.

First claim

What is claimed is:

1. A turboprop propulsion system adapted for use in an airplane having an airframe, the turboprop propulsion system adapted for fixed connection to the airframe, the system comprising:
a propeller mounted for rotation about a propeller axis,
a gas turbine engine mounted to establish an engine axis of rotation different from the propeller axis to form an offset angle therebetween, and
a gearbox coupled between the propeller and the gas turbine engine and configured to accommodate the offset angle between the propeller axis and the engine axis of rotation,
wherein the propeller axis and the engine axis of rotation are fixed with respect to each and are located within a single nacelle.

2. The turboprop propulsion system of claim 1 , wherein the offset angle is between 10 degrees and 15 degrees.

3. The airplane of claim 1 , wherein the nacelle includes an inlet duct shaped to provide a direct line of sight from an inlet of the gas turbine engine to an engine-air-entry aperture of the nacelle.

4. The turboprop propulsion system of claim 1 , wherein the nacelle houses the gas turbine engine, the nacelle including an exhaust duct shaped to provide a direct line of sight from an exhaust discharge outlet of the gas turbine engine to an exhaust-outlet aperture of the nacelle.

5. The turboprop propulsion system of claim 4 , further comprising an infrared suppressor coupled to the gas turbine engine and configured to conduct exhaust gasses at least part way from the exhaust discharge outlet of the gas turbine engine to the exhaust-outlet aperture of the nacelle, wherein the infrared suppressor has a direct line of sight from the exhaust discharge outlet of the gas turbine engine to the exhaust-outlet aperture of the nacelle.

6. The turboprop propulsion system of claim 4 , wherein the inlet duct has a Y-shape having first and second portions that extend to respective ones of two engine-air-entry apertures and a third portion that extends to the inlet of the gas turbine engine and direct lines of sight are provided from the inlet of the gas turbine engine to both of the engine-air-entry apertures.

7. An airplane comprising
an airframe including a fuselage and a wing coupled to the fuselage, and
a turboprop propulsion system coupled to the wing to provide thrust for the airplane, the turboprop propulsion system including a propeller mounted for rotation about a propeller axis and a gas turbine engine coupled to the propeller to drive the propeller about the propeller axis,
wherein the gas turbine engine is mounted to establish an engine axis of rotation different from the propeller axis and form an offset angle between the propeller axis and the engine axis of rotation,
wherein the propeller axis and the engine axis of rotation are fixed with respect to each other and are located within a single nacelle, and
wherein the engine axis of rotation and the propeller axis are fixed with respect to the airframe.

8. The airplane of claim 7 , wherein the nacelle houses the gas turbine engine, and wherein the nacelle includes an inlet duct shaped to provide a direct line of sight from an inlet of the gas turbine engine to an engine-air-entry aperture of the nacelle.

9. The airplane of claim 7 , wherein the nacelle houses the gas turbine engine and an infrared suppressor coupled to the gas turbine engine, the infrared suppressor is configured to conduct exhaust gasses at least part way from an exhaust discharge outlet of the gas turbine engine to an exhaust-outlet aperture of the nacelle, and the infrared suppressor has a direct line of sight from the exhaust discharge outlet of the gas turbine engine to an exhaust-outlet aperture of the nacelle.

10. The airplane of claim 9 , wherein the nacelle is formed to include a suppressor-air aperture configured to conduct air to the infrared suppressor during use of the turboprop propulsion system and an engine-air-entry aperture configured to conduct air to the gas turbine engine during use of the turboprop propulsion system, and wherein the suppressor-air aperture is spaced apart from an engine-air-entry aperture.

11. The airplane of claim 7 , wherein the gas turbine engine is mounted such that a vector of exhaust gasses discharged from the gas turbine engine during use has a downward component that provides lift to the airplane relative to the ground when the airplane is landed on the ground when the turboprop propulsion system is in use.

12. The airplane of claim 11 , wherein the offset angle is between 10 degrees and 15 degrees.

13. The airplane of claim 7 , wherein the turboprop propulsion system includes a gearbox coupled between the propeller and the gas turbine engine and configured to accommodate the offset angle between the propeller axis and the engine axis of rotation by coupling to the propeller mounted for rotation about the propeller axis and to an output shaft of the gas turbine engine adapted to rotate about the engine axis of rotation.

14. The airplane of claim 13 , wherein the nacelle houses the gas turbine engine and at least part of the gearbox.

15. The airplane of claim 7 , wherein the nacelle houses the gas turbine engine, the nacelle including an exhaust duct shaped to provide a direct line of sight from an exhaust discharge outlet of the gas turbine engine to an exhaust-outlet aperture of the nacelle.

16. The airplane of claim 15 , wherein the turboprop propulsion system includes an infrared suppressor coupled to the gas turbine engine and configured to conduct exhaust gasses at least part way from the exhaust discharge outlet of the gas turbine engine to the exhaust-outlet aperture of the nacelle, wherein the infrared suppressor has a direct line of sight from the exhaust discharge outlet of the gas turbine engine to the exhaust-outlet aperture of the nacelle.

17. The airplane of claim 15 , wherein the nacelle includes an inlet duct shaped to provide a direct line of sight from an inlet of the gas turbine engine to an engine-air-entry aperture of the nacelle.

18. The airplane of claim 17 , wherein the turboprop propulsion system includes a heat exchanger housed in the nacelle and the nacelle is formed to include a cooling-air aperture through which air flows to the heat exchanger during use of the turboprop propulsion system and the cooling-air aperture is spaced apart from the engine-air-entry aperture of the nacelle.

19. The airplane of claim 18 , wherein the heat exchanger is arranged below the gas turbine engine when the airplane is landed on the ground.

Assignees

• Rolls Royce Nam Tech Inc

Inventors

• Keller Richard K

Classifications

• B64D33/08

  of power plant cooling systems · CPC title

• B64D33/04

  of exhaust outlets or jet pipes · CPC title

• F01D15/12

  Combinations with mechanical gearing (driven by multiple engines F01D13/00) · CPC title

• B64D2033/045

  comprising infrared suppressors · CPC title

• F01D25/30

  Exhaust heads, chambers, or the like · CPC title