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Visual observation and transient measurement method and apparatus for cooling process of turbine blade

A technology of turbine blade and cooling process, applied in the field of devices for realizing the above method

Active Publication Date: 2009-03-25
中科思道(南京)储能技术有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The cooling of aviation turbine blades is mainly achieved through the joint action of internal flow cooling and external film cooling. There are reports on the combination of internal flow cooling and film cooling

Method used

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  • Visual observation and transient measurement method and apparatus for cooling process of turbine blade
  • Visual observation and transient measurement method and apparatus for cooling process of turbine blade
  • Visual observation and transient measurement method and apparatus for cooling process of turbine blade

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Embodiment Construction

[0032] see figure 1 and figure 2 , is a schematic diagram of the testing device of the present invention.

[0033] The present invention mainly consists of a blower 1, a heater 2, a wind tunnel 3, a turbine blade 4, an infrared detection window 5, a visual observation window 6, an air compressor 7, an infrared thermal imager 8, a microscopic magnifying photographic device 9, temperature and pressure And flow measurement and data acquisition and recording device 10, flow regulating valves 11 and 12, paint adding device 13 and cold air pipe 14.

[0034] Among them, the flow rate of blower 1 is 0-850m 3 / h is adjustable; the heater 2 is electric heating, and the power is adjustable from 0-3000W. By adjusting the power of the heater, the temperature of the mainstream hot air can be adjusted within the range of 20-500°C.

[0035] The wind tunnel 3 is a cuboid made of stainless steel with a length of 3500mm and a section of 100×100mm. One end of the wind tunnel 3 is connected w...

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Abstract

The invention relates to a method for carrying out visual observation and transient measurement on a cooling process of a turbine blade, which comprises the following steps: heating main flow air to a pre-determined temperature; introducing cold air flow; allowing the cold air flow to enter to a cooling passage inside the turbine blade first to cool the blade; and allowing the cold air flow to flow to the surface of the turbine blade to form a layer of a cold air film; and recording the temperature and the pressure of each measuring point and observing the conditions of mixing and flowing of the main flow and the cold air flow near the turbine blade. A device for realizing the method comprises an air tunnel, one end of the air tunnel is connected with a hot air source, while the other end is an exhaust port; the turbine blade is placed inside the air tunnel according to an operating state of the blade; a cold air source connected with a jet pipe of the turbine blade in the air tunnel through an air pipe; a pigment feeding device is arranged on the air pipe; infrared probing windows are respectively arranged on two sides of the air tunnel which is positioned in the turbine blade; the infrared probing windows are respectively provided with infrared thermal imagers; visual observing windows are respectively arranged on the two sides of the air tunnel which is positioned in the turbine blade; and the visual observing windows are respectively provided with micro-amplifying photographic devices.

Description

technical field [0001] The invention relates to a method for visual observation and transient measurement of supernormal flow and heat transfer in the microscale cooling process of turbine blades of a gas turbine. [0002] The invention also relates to a device for implementing the above method. Background technique [0003] The turbine blades of aviation gas turbines have a complex structure and work under the harsh conditions of high temperature, high pressure, and high speed for a long time, but they also require the technical characteristics of "high performance, high reliability, low fuel consumption, low cost, and long life". The development is difficult, requires a lot of investment, and has a long cycle, involving many disciplines such as machinery, materials, electronics, mechanics, acoustics, thermals, energy, and management. [0004] Along with the development trend of improving the thrust and thermal efficiency of the turbine engine by increasing the inlet gas t...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M9/06G01M19/00G01M99/00
Inventor 淮秀兰陶毓伽梁世强蔡军顾维藻
Owner 中科思道(南京)储能技术有限公司
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