Aircraft powerplant

Patent metadata

Field	Value
Publication number	US-9637240-B2
Application number	US-201414228854-A
Country	US
Kind code	B2
Filing date	Mar 28, 2014
Priority date	Apr 24, 2013
Publication date	May 2, 2017
Grant date	May 2, 2017

Abstract

An aircraft propulsion power plant for use in an aircraft includes one or more core engines housed in an airframe of the aircraft, one or more secondary propulsion units, each of the one or more secondary propulsion units being removably attached to the airframe, and one or more power transmission means, each of the one or more power transmission means being configured to transmit mechanical power from the or each core engine to a corresponding one of the or each secondary propulsion unit when the or each secondary propulsion unit is attached to the airframe.

First claim

What is claimed is:

1. An aircraft propulsion power plant for use in an aircraft comprising:
one or more core engines housed in an airframe of the aircraft;
one or more secondary propulsion units, each of the one or more secondary propulsion units being removably attached to the airframe;
one or more power transmission means, each of the one or more power transmission means being configured to transmit mechanical power from the or each core engine to a corresponding one of the or each secondary propulsion unit when the or each secondary propulsion unit is attached to the airframe; and
an engine control unit adapted to control the operation of the or each core engine by actively altering one or more engine control parameters in dependence on whether the or each secondary propulsion unit is attached to the airframe.

2. The power plant as claimed in claim 1 , wherein the or each core engine comprises a turbofan engine and the turbofan engine comprises a low pressure spool.

3. The power plant as claimed in claim 2 , wherein the or each power transmission means is configured to transmit mechanical power from the low pressure spool of the or each core engine to a corresponding one of the or each secondary propulsion unit.

4. The power plant as claimed in claim 2 , wherein the turbofan engine comprises a variable area exhaust nozzle.

5. The power plant as claimed in claim 2 , wherein the turbofan engine comprises a removably attached exhaust nozzle.

6. The power plant as claimed in claim 1 , wherein the or each secondary propulsion unit comprises a propeller.

7. The power plant as claimed in claim 6 , wherein the propeller is a variable pitch propeller.

8. The power plant as claimed in claim 1 , wherein the or each secondary propulsion unit comprises a ducted fan.

9. The power plant as claimed in claim 8 , wherein the fan is a variable pitch fan.

10. The power plant as claimed in claim 1 , wherein the or each power transmission means comprises an electrical generator attached to the or each core engine, an electrical power transmission means and an electric motor mounted within each of the one or more secondary propulsion units, and
the or each electrical generator being adapted to generate an electrical current during operation of the or each core engine, and the or each electrical power transmission means being adapted to transmit the electrical current to the or each corresponding electric motor.

11. The power plant as claimed in claim 10 , wherein the or each electrical generator is driven from the low pressure spool of the turbofan engine.

12. The power plant as claimed in claim 1 , wherein the or each power transmission means comprises a driveshaft being in coupling engagement at a first end thereof with the or each core engine and at a second end thereof with the or each corresponding secondary propulsion unit.

13. The power plant as claimed in claim 12 , the or each driveshaft comprising:
a first portion accommodated within the airframe of the aircraft; and
a second portion accommodated within the or each corresponding secondary propulsion unit;
wherein each first portion is removably coupled to each respective second portion.

14. The power plant as claimed in claim 1 , wherein the engine control parameters comprise one or more parameters selected from the group comprising:
fuel flow rate;
compressor air bleed volume;
exhaust nozzle area
variable stator geometry; and
variable vane geometry.

15. The power plant as claimed in claim 1 , further comprising a convoluted air inlet duct being in fluid communication with an inlet face of the core engine such that there is no direct line of sight through the duct.

16. The power plant as claimed in claim 1 , wherein each of the one or more secondary propulsion units comprises a pylon connecting the respective secondary propulsion unit to the airframe, a respective one of the one or more power transmission means being located within the corresponding pylon.

17. A method of configuring an aircraft comprising the steps of:
a. providing an airframe having a power plant as claimed in claim 1 ;
b. attaching to the airframe a first lifting surface if the or each secondary propulsion unit is attached to the airframe; and
c. alternatively, attaching to the airframe a second lifting surface if the or each secondary propulsion unit is not attached to the airframe.

18. The method as claimed in claim 17 , wherein the first lifting surface comprises a pair of high aspect ratio wings.

19. The method as claimed in claim 17 , wherein the first lifting surface comprises a pair of low aspect ratio wings.

20. The method as claimed in claim 17 , the aircraft comprising an engine control unit, wherein step b comprises the additional step of:
b1. providing the engine control unit with a first set of pre-determined control parameters;
and step c comprises the additional step of:
c1. providing the engine control unit with a second set of pre-determined control parameters.

Assignees

• Rolls Royce Plc

Inventors

• Bradbrook Stephen John

Classifications

• B64D35/024

  of series type · CPC title

• B64D27/14 Primary

  within, or attached to, fuselages · CPC title

• B64D35/023

  of series-parallel type · CPC title

• B64D31/18

  for hybrid-electric power plants · CPC title

• B64D31/16

  for electric power plants · CPC title