Method for optimising the specific consumption of a twin helicopter

An optimization method, helicopter technology, applied in the direction of engine components, machines/engines, rotorcraft, etc., to achieve the effect of reducing fuel consumption, temperature and fuel consumption reduction

Active Publication Date: 2016-05-18
TURBOMECA SA
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Since the flow rate of the gas circulation in the generator is lower at super-idle, the temperature of the generator is relatively hotter than during take-off and this can cause problems with regard to cooling and thus the service life of the components

Method used

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  • Method for optimising the specific consumption of a twin helicopter

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Embodiment Construction

[0023] The terms "engine" and "turboshaft engine" are used synonymously in this document. In the illustrated embodiment, the engines have different maximum powers. Advantageously, this embodiment makes it possible to suppress the OEI speed on the more powerful turboshaft engine, and this minimizes the difference in mass between the two engines. To simplify language, the most powerful engine or oversized engine may also be referred to as a "large" engine, while the smallest powered engine may be referred to as a "small" engine.

[0024] The drawings schematically show an example of a structure of a twin-engine helicopter capable of optimizing the specific consumption Cs.

[0025] Typically, each turboshaft engine 1 , 2 comprises a gas generator 11 , 21 and a free turbine 12 , 22 fed by the gas generator to provide power. During takeoff and at continuous speed, the power supplied may reach predetermined maximum values ​​PMD and PMC, respectively. In general, a gas generator c...

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Abstract

The invention relates to a method for optimising the specific consumption of a helicopter provided with two turboshafts (1, 2), each one comprising a gas generator (11, 21) provided with a combustion chamber (CC), each of said turboshafts (1, 2) being able to operate alone in the continuous flight mode, the other turboshaft (2, 1) being then in a so-called super-slow mode with zero power and with the combustion chamber lit, said super-slow mode being assisted by a mechanical rotation of the shaft (AE) of the gas generator in this mode, in such a way as to reduce the operating temperature and the fuel consumption of said gas generator.

Description

technical field [0001] The invention relates to a method for optimizing the specific consumption of a twin-engine helicopter, ie a helicopter equipped with two turboshaft engines. Background technique [0002] Typically, a turboshaft engine operates at a low power level below its maximum continuous power (PMC) when flying at cruising speeds. At cruising speed, the power is equal to about 50% of their maximum takeoff power (PMD). These low power levels result in a specific consumption Cs (specific consumption) approximately 30% higher than in PMD and thus lead to excessive consumption of fuel at cruising speeds. [0003] The helicopter is equipped with two turboshaft engines, each oversized to keep the helicopter in the air if the other fails. in those operating modes dedicated to managing a failed engine (known as one engine inoperative (OEI) mode), the still-running engine provides power well above its rated power in order to enable the helicopter to deal with hazardous s...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02C6/20F02C9/44
CPCF02C6/206F02C9/44Y02T50/60B64C27/12F01D15/08F01D15/12F02C3/04F02C7/262F02C9/42F05D2220/329F05D2240/35B64C27/04B64D27/10
Inventor 帕垂克·马考尼罗曼·蒂里耶
Owner TURBOMECA SA
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