Power plant including a secondary engine for compensating for losses of power from main engines in a rotary wing aircraft

Patent metadata

Field	Value
Publication number	US-9890708-B2
Application number	US-201414577254-A
Country	US
Kind code	B2
Filing date	Dec 19, 2014
Priority date	Dec 20, 2013
Publication date	Feb 13, 2018
Grant date	Feb 13, 2018

Abstract

A method of managing a power plant for a rotary wing aircraft, said power plant comprising two main engines, a secondary engine, and a main power transmission gearbox (MGB). Said main and secondary engines mechanically driving said MGB so as to rotate a main rotor of said aircraft. Said secondary engine delivers two distinct mechanical power levels so that said main and secondary engines together deliver sufficient mechanical power to enable said aircraft to fly, firstly a first secondary mechanical power MP S1 and secondly a second secondary mechanical power MP S2 suitable for compensating for a loss of main mechanical power from at least one main engine.

First claim

What is claimed is:

1. A method of managing a power plant for a rotary wing aircraft, the power plant comprising at least two main engines, at least one secondary engine, and a main power transmission gearbox (MGB), the main and secondary engines driving the MGB mechanically in order to rotate at least one main outlet shaft the MGB, the main outlet shaft being constrained to rotate with a main rotor of the aircraft, each main engine being capable of delivering continuously a first main mechanical power that is less than or equal to a maximum continuous main mechanical power MCP M and of delivering temporarily an emergency second main mechanical power that is greater than or equal to a guaranteed minimum emergency main mechanical power OEIP MIN , each secondary engine being capable of delivering continuously a secondary mechanical power that is less than or equal to a maximum continuous secondary mechanical power MCP S , the method being characterized by the following steps:
performing an engine health check on each main engine determining a level of degradation of each main engine and a main mechanical power margin CSM P11 , CSM P12 for each main engine;
determining a coefficient K as being greater than or equal to zero where:
K =|min[0, CSM P11 ,CSM P12 ]|

CSM P11 and CSM P12 being the main mechanical power margins of each of the main engines respectively, “0” being the value zero, “min” being a function returning the minimum value from among a series of values, and “| |” being the absolute value function;
controlling each main engine to deliver a main mechanical power; and
controlling each secondary engine to deliver two distinct mechanical power levels, the secondary mechanical power level delivered by each secondary engine enabling each main engine and each secondary engine to act together to deliver mechanical power that is greater than or equal to sufficient mechanical power SMP for enabling the aircraft to fly using the main rotor, the two secondary mechanical power levels being a first secondary mechanical power MP S1 and a second secondary mechanical power MP S2 , the second secondary mechanical power MP S2 being:
MP S2 =MP S1 K·P det

where P det is a predetermined main mechanical power value and “·” is the multiplication function, the second secondary mechanical power MP S2 thus serving to compensate for a loss of main mechanical power in at least one main engine.

2. The method according to claim 1 for managing a power plant, wherein the maximum continuous secondary mechanical power MCP S delivered by each secondary engine is less than the maximum continuous main power MCP P of each main engine.

3. The method according to claim 1 for managing a power plant, wherein the main mechanical power margin CSM P11 , CSM P12 of a main engine is a margin relating to the guaranteed minimum emergency main mechanical power OEIP MIN of each main engine such that:

CSM

P
⁢

⁢
11

=

OEIP
Avail

-

OEIP
MIN

OEIP
MIN

where OEIP MIN is the guaranteed minimum emergency main mechanical power of the main engine, and OEIP Avail is an available emergency main mechanical power of the main engine.

4. The method according to claim 1 for managing a power plant, wherein the predetermined main mechanical power P det is the guaranteed minimum emergency main mechanical power OEIP MIN of a main engine.

5. The method according to claim 1 for managing a power plant, wherein the predetermined main mechanical power P det is a percentage of the maximum continuous main mechanical power MCP P of a main engine.

6. The method according to claim 1 for managing a power plant, wherein each main engine possesses a maximum takeoff main mechanical power TOP M and the predetermined main mechanical power P det is a percentage of the maximum takeoff main mechanical power TOP M of a main engine.

7. The method according to claim 1 for managing a power plant, wherein the predetermined main mechanical power P det is associated with the main engine having the smallest the main mechanical power margin CSM P11 , CSM P12 .

8. The method according to claim 1 for managing a power plant, wherein an operator can control each secondary engine to deliver the second secondary mechanical power MP S2 .

9. The method according to claim 1 for managing a power plant, wherein the second secondary mechanical power MP S2 of each secondary engine may be an emergency secondary mechanical power.

10. The method according to claim 1 for managing a power plant, wherein the second secondary mechanical power MP S2 is constant between two engine health checks of each main engine.

11. The method according to claim 1 for managing a power plant, wherein the first secondary mechanical power MP S1 is constant.

12. The method according to claim 1 for managing a power plant, wherein the first and second secondary mechanical powers MP S1 , MP S2 are power limits for each secondary engine.

13. The method according to claim 1 for regulating a power plant, wherein each secondary engine is controlled so that the secondary mechanical power is zero when the aircraft is in cruising flight.

14. The method according to claim 1 for managing a power plant, wherein the power plant has two identical main engines and only one secondary engine.

15. A power plant for a rotary wing aircraft, the power plant comprising at least two main engines, at least one secondary engine, at least one calculation unit, an engine control unit, and a main power transmission gearbox (MGB), the main and secondary engines driving the MGB mechanically in order to rotate at least one main outlet shaft of the MGB, the main outlet shaft being suitable for being constrained to rotate with a main rotor of the aircraft, each main engine being capable of delivering continuously a first main mechanical power that is less than or equal to a maximum continuous main mechanical power MCP M and of delivering temporarily an emergency second main mechanical power that is greater than or equal to a guaranteed minimum emergency main mechanical power OEIP MIN , each secondary engine being capable of delivering continuously a secondary mechanical power that is less than or equal to a maximum continuous secondary mechanical power MCP S ,
wherein said the engine control unit is configured to perform the method in accordance with claim 1 for managing the power plant.

16. A rotary wing aircraft including at least one main rotor and a power plant, the power plant driving the main rotor in rotation, wherein the power plant is a power plant in accordance with claim 15 .

Assignees

• Airbus Helicopters

Inventors

• Borchers Guido
• Stephant Romain

Classifications

• B64D31/06

  actuated automatically · CPC title

• F05D2220/329

  in helicopters · CPC title

• F02C6/02 Primary

  Plural gas-turbine plants having a common power output · CPC title

• F02C7/36

  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 title

• Y02T50/671

  Cross-Sectional Technologies · mapped topic