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System for controlling variable geometry apparatuses of a gas turbine engine particularly comprising a barrel link

A gas turbine and engine technology, which is applied in gas turbine devices, mechanical equipment, engine components, etc., can solve the problems of increased risk of engine flameout and large drawbacks.

Active Publication Date: 2013-12-04
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

Although the savings achieved by this approach are great (the associated transmission, servo valves, conduits, wiring harnesses, etc. are omitted), the disadvantages are also great, especially at idle, if water or hail enters the engine increases the risk of engine stalling

Method used

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  • System for controlling variable geometry apparatuses of a gas turbine engine particularly comprising a barrel link
  • System for controlling variable geometry apparatuses of a gas turbine engine particularly comprising a barrel link
  • System for controlling variable geometry apparatuses of a gas turbine engine particularly comprising a barrel link

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Embodiment Construction

[0056] well known, such as figure 1 and figure 2 As shown, a gas turbine engine suitable for the aerospace field, such as a jet engine (represented by the X-X axis here), includes a fan, a low-pressure compressor 2, a high-pressure compressor 4, a combustor, a high-pressure turbine, and a low-pressure turbine from upstream to downstream and nozzles for injecting gas (not shown in the figure). The compressor and the high-pressure turbine are firmly fixed to the same shaft, called the high-pressure shaft, and thus belong to the high-pressure body of the engine or the first body that rotates at the first speed, while the low-pressure compressor and the low-pressure turbine are firmly fixed to the same shaft shaft, called the low-pressure shaft, and therefore belongs to the low-pressure body of the engine or the second body rotating at the second speed.

[0057] In the following, the abbreviations LP and HP denote low pressure and high pressure, respectively.

[0058] The high...

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Abstract

A system for controlling at least two variable geometry apparatuses of a gas turbine engine that includes at least a first body and a second body, the first apparatus including a stator blade stage with a variable setting angle of a compressor of the first body capable of switching between a closed position in an idle mode and an open position in a high-speed mode, and the second apparatus including at least one discharge valve of a compressor of the second body capable of switching between an open position in an idle mode and a closed position in a high-speed mode. The system further includes an actuator for actuating the two apparatuses.

Description

technical field [0001] The present invention relates to the general field of variable geometry plant control of gas turbine engines, especially jet engines. In particular, the invention relates to the optimization of the control of several pieces of equipment constituting the individual components of a gas turbine engine. Background technique [0002] The term "variable geometry equipment item" shall be understood here as a device connected to a control member, and the size, shape, position and / or rotational speed of the device can be changed according to detected events or determined parameters. modified so as to have an effect on the operation of the engine. Examples of variable geometry devices include compressor discharge valves (with variable opening), fixed compressor vanes with variable set angles, turbine vanes with variable tip clearance, variable flow fuel pumps, and more. [0003] The term "body" refers to an assembly of a gas turbine engine, comprising, as main...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F01D17/16F01D17/20F02C6/08F02C9/18F02C9/22
CPCF02C9/22F01D17/16F02C9/18Y02T50/671F01D17/20F05D2270/58F02C6/08Y02T50/60F04D27/023F04D27/0246F04D27/0215
Inventor 巴普蒂斯特·贝努特·科洛特布鲁诺·罗伯特·加利
Owner SN DETUDE & DE CONSTR DE MOTEURS DAVIATION S N E C M A
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