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Turbine guide blade and heat exchange structure thereof

A technology of turbine guide vanes and heat exchange structure, which can be used in stators, engine components, machines/engines, etc., and can solve problems such as large airflow consumption

Inactive Publication Date: 2017-08-11
AECC HUNAN AVIATION POWERPLANT RES INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0006] It is an object of the present disclosure to provide a turbine guide vane that overcomes, at least to some extent, the problem of large airflow consumption due to the limitations and drawbacks of the related art

Method used

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  • Turbine guide blade and heat exchange structure thereof
  • Turbine guide blade and heat exchange structure thereof

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Embodiment Construction

[0028] Example embodiments will now be described more fully with reference to the accompanying drawings. Example embodiments may, however, be embodied in many forms and should not be construed as limited to the examples set forth herein; rather, these embodiments are provided so that this disclosure will be thorough and complete and will fully convey the concept of example embodiments to those skilled in the art. The described features, structures, or characteristics may be combined in any suitable manner in one or more embodiments. In the following description, numerous specific details are provided in order to give a thorough understanding of embodiments of the present disclosure. However, those skilled in the art will appreciate that the technical solutions of the present disclosure may be practiced without one or more of the specific details being omitted, or other methods, components, devices, steps, etc. may be adopted. In other instances, well-known technical solution...

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Abstract

The disclosure relates to a turbine guide vane and its heat exchange structure, and relates to the technical field of turbine engine cooling. The heat exchange structure of the turbine guide vane disclosed in the present disclosure is applied in the chamber between the turbine guide vane edge plate and the casing, and is exchanged The thermal structure includes: a plurality of air intake holes, a plurality of air outlet holes, and a spoiler column arranged between the air inlet holes and the air outlet holes; among them, a plurality of air inlet holes are opened on the wall surface of the casing near the front end of the chamber, and the low-temperature gas It is sent to the chamber through the air inlet; multiple air outlet holes are opened on the wall of the guide vane edge plate near the rear end of the chamber, and the low-temperature gas after heat exchange is sent out through the air outlet; the spoiler column is set in the chamber, and the low-temperature gas enters After the chamber, heat is exchanged through spoiler columns. On the one hand, it can increase the heat transfer area and heat transfer coefficient of the edge plate of the guide vane, strengthen the heat transfer effect, and prevent the ablation of the edge plate; on the other hand, it can improve the cooling efficiency, and use the same or less cooling air to further reduce Adverse effects on performance.

Description

technical field [0001] The present disclosure relates to the technical field of turbine engine cooling, in particular, to a turbine guide vane and a heat exchange structure thereof. Background technique [0002] In gas turbine engines and ground gas turbines in the related art, due to the high temperature of the gas in the turbine flow passage, especially the maximum temperature at the turbine inlet may reach 1500°C, the working environment of the turbine guide vanes is very harsh. The edge plates of the guide vanes need to be cooled to prevent ablation. The usual way is to let the gas with lower temperature in the engine flow through the edge plate of the guide vane, and take away the heat on the edge plate during the circulation of the low-temperature gas, so as to reduce the temperature of the edge plate of the guide vane. [0003] In the engine, the amount of low-temperature gas, that is, cold air, is an important indicator that affects engine performance. In order to ...

Claims

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Application Information

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IPC IPC(8): F01D9/04F01D25/12
CPCF01D9/041F01D25/12F05D2240/12F05D2260/22141
Inventor 叶炜付晟白忠恺蔡琴陈润拓蔡斌
Owner AECC HUNAN AVIATION POWERPLANT RES INST
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