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Device for cutting-off of power to the alternators of a turbine engine during acceleration

A technology for turbine engines and generators, applied in the direction of electromechanical devices, battery circuit devices, auxiliary power equipment, etc., can solve the problems of increasing HP compressors, surge margin requirements, etc.

Active Publication Date: 2015-12-09
SN DETUDE & DE CONSTR DE MOTEURS DAVIATION S N E C M A
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the increase in mechanical power drawn from the HP drive shaft to power the generator creates an inrush headroom requirement for the HP compressor

Method used

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  • Device for cutting-off of power to the alternators of a turbine engine during acceleration
  • Device for cutting-off of power to the alternators of a turbine engine during acceleration
  • Device for cutting-off of power to the alternators of a turbine engine during acceleration

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Embodiment Construction

[0023] figure 1 A conventional circuit for an aircraft such as a twin engine jet aircraft is shown. Each engine drives a variable frequency generator marked G1 and G2 respectively, the alternating current provided by the variable frequency generator is then distributed by means of AC (Alternating Current) buses BusAC1 (bus AC1) and BusAC2 (bus AC2) to the entire aircraft. These two buses feed a single AC bus, BusAC, to which pieces of equipment of the aircraft, which are consumers of AC power, are connected.

[0024] Furthermore, the aircraft has two battery packs BAT1 (Battery Pack 1) and BAT2 (Battery Pack 2), which supply DC (DirectCurrent, Direct Current) for an electrical bus referred to here as BusDC (Bus DC). Electric current, this electrical bus connects the various pieces of equipment of the aircraft, which in turn are consumers of DC electrical energy. In addition, the DC-AC converter StatInv enables the battery packs BAT1, BAT2 to supply the BusAC with alternatin...

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PUM

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Abstract

The present invention pertains to a DC electrical generation system for an aircraft propelled by a turbine engine, such as a turbojet, comprising at least one electrical energy storage capacity (BAT 1, BAT 2), at least one generator (G1, G2) driven mechanically by a rotation shaft of the turbine engine and electrical connections between the electrical energy storage capacity, the generator and the aircraft equipment for powering the above-mentioned equipment with DC current, also comprising at least one alternative means for supplying DC current (SUP 1, SUP 2) to said equipment, which means are autonomous in relation to any mechanical driving by a rotation shaft of the turbine engine, and a device (CONT) that can cut-off power to the generator(s) and simultaneously activate the alternative means. The system is characterized in that the power cut-off device (CONT) for triggering power cut-off and activating the alternative current supply means is controlled by a control or operating parameter of the turbine engine. The alternative current supply means is preferably formed by one or more supercapacitors.

Description

technical field [0001] The present invention relates to the field of turbine engines, and in particular to a system for supplying electrical power to equipment of an aircraft, the system being installed on board the aircraft. Background technique [0002] From the start-up phase, the equipment of the aircraft is usually powered by drawing power from the engines that provide the aircraft's propulsion. The electrical power is generated by a generator commonly known as a variable frequency generator (VFG) or integrated drive generator (IDG), which is mechanically driven by a drive shaft attached to one rotor of the turbine engine. This electrical extraction affects the thermodynamic operation of the engine, and it is desirable to optimize the overall generation of electrical power on the aircraft to optimize the design of the turbine engine. [0003] The trend in recent aircraft is to have, on the one hand, reducing the size of the high-pressure body of the turbojet engine to ...

Claims

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Application Information

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IPC IPC(8): B64D41/00
CPCB64D41/00B64D2221/00H02J4/00H02J7/1415H02J7/1423H02J7/1446H02J7/345H02J2007/143H02J7/143H02J2310/44Y02T50/40H02J9/00F01D15/10F05D2220/323H02K7/1823H02P9/008H02P9/48
Inventor 阿诺·勒布伦托马斯·莱帕赫达雷格·麦克格拉斯
Owner SN DETUDE & DE CONSTR DE MOTEURS DAVIATION S N E C M A