Method of optimizing the specific fuel consumption of a twin engine helicopter and twin engine architecture with control system for implementing it

A technology of fuel consumption rate, optimization method, applied in the direction of engine components, machine/engine, turbine/propulsion fuel delivery system, etc., can solve problems such as the danger of engine landing

Active Publication Date: 2013-09-18
TURBOMECA SA
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

Landing with a faulty engine can be dangerous if the backup engine does not start in time

Method used

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  • Method of optimizing the specific fuel consumption of a twin engine helicopter and twin engine architecture with control system for implementing it
  • Method of optimizing the specific fuel consumption of a twin engine helicopter and twin engine architecture with control system for implementing it
  • Method of optimizing the specific fuel consumption of a twin engine helicopter and twin engine architecture with control system for implementing it

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Embodiment Construction

[0042] In the present specification, the terms "engine" and "turbine engine" are used synonymously. In the illustrated embodiment, the engines have different maximum powers from each other. Advantageously, the described embodiment eliminates the one engine inactive (OEI) speed of the most powerful turbine engine, thereby minimizing the difference in mass between the two engines. To simplify language, the most powerful engines or oversized engines are also referred to as "large" engines, and the least powerful engines are also referred to as "small" engines.

[0043] figure 1 The schematic diagram shows the change of the total power Pw required by the twin-engine helicopter at different times "t" when performing rescue missions for shipwrecked personnel. This task consists of six main phases:

[0044] Takeoff phase "A" using maximum takeoff power (MTOP);

[0045] Cruise flight phase "B" for transit to the search area, during which the power level is less than or equal to th...

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Abstract

The invention seeks to reduce the specific fuel consumption Cs of a twin engine helicopter without compromising on the safety conditions regarding the minimum amount of power to be supplied for any kind of mission. To achieve this, the invention plans to make available special means capable of guaranteeing reliable in-flight restarts. One example of an architecture according to the invention involves two turbine engines (1, 2) each equipped with a gas generator (11, 21) and a with a free turbine (12, 22). Each gas generator (11, 21) is equipped with active drive means (E1, E2) capable of keeping the gas generator (1, 21) rotating with the combustion chamber inactive, and an emergency assistance device (U1, U2) comprising near-instantaneous firing means and mechanical means for accelerating the gas generator (11, 21).; The control system (4) controls the drive means (E1, E2) and the emergency assistance devices (U1, U2) for the gas generators (11, 21) according to the conditions and phases of flight of the helicopter following a mission profile logged beforehand in a memory (6) of this system (4).

Description

technical field [0001] The present invention relates to a method for optimizing the specific fuel consumption (Cs) of a helicopter equipped with two turbine engines, and a twin-engine configuration equipped with a control system for implementing this method. [0002] Typically, at cruising power, at its maximum continuous power, referred to as MCP (Maximum Continuous Power), the turbine engine operates at low power. This cruise power is equal to about 50% of its maximum take-off power (MTOP for short). The result of this low power operation is that the specific fuel consumption is about 30% higher than the specific fuel consumption at maximum take-off power (MTOP), and therefore, at cruising power, the fuel consumption is excessive. [0003] The helicopter is equipped with two turbine engines, each of which is oversized to keep the helicopter in flight should the other engine fail. At this operating power dedicated to managing the inactive engine, the so-called OEI (One Engi...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02C6/20F02C9/44
CPCF02C6/206F02C7/268F02C9/44Y02T50/60F02C6/20F02C5/00
Inventor 帕特里克·马尔科尼罗曼·希尔瑞特
Owner TURBOMECA SA
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