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Total temperature probe device with high precision and low self-loss

A technology with high precision and total temperature, applied in the field of rotating machinery blades, to achieve the effect of reducing flow loss

Pending Publication Date: 2019-08-23
ZHEJIANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Installing a temperature probe in the flow field will bring additional losses, so it must be considered to minimize the impact of the device on the loss, so as to ensure that the thermal efficiency calculated by the temperature probe is not much different from the real thermal efficiency

Method used

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  • Total temperature probe device with high precision and low self-loss
  • Total temperature probe device with high precision and low self-loss
  • Total temperature probe device with high precision and low self-loss

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Embodiment Construction

[0019] In order to make the purpose, technical solution and advantages of the present invention clearer, the low-pressure turbine blade of the present invention will be described in detail below with reference to the drawings and specific embodiments.

[0020] like Figure 1-5 As shown, the present invention provides a total temperature probe device with low self-loss and high precision. The total temperature probe device is installed on the blade leading edge of the rotating mechanical blade of an aerospace vehicle. The total temperature probe device includes a probe body, a probe There are two layers of chambers on the body, respectively marked as stagnation layer 2 and heat insulation layer 3. The heat insulation layer 3 is set outside the stagnation layer 2. The stagnation layer 2 contains the temperature sensor 1, the stagnation layer 2 and A first through hole 4 is opened between the heat insulating layers 3 , and a second through hole 5 is opened at the bottom of the he...

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Abstract

The invention discloses a total temperature probe device with high precision and low self-loss. The total temperature probe device is installed at the leading edge of a rotating mechanical blade of anaerospace vehicle and comprises a probe body, wherein the probe body is defined with two layers of chambers, which are respectively recorded as a stagnation layer and a heat insulation layer; the heat insulation layer is sleeved outside the stagnation layer, the stagnation layer contains a temperature sensor, a first through hole is defined between the stagnation layer and the heat insulation layer, and a second through hole is defined at the bottom of the heat insulation layer in the direction of the blade pitch. The purpose of the total temperature measuring device provided by the inventionis to accurately measure the stagnation temperature of the leading edge of the blade, reduce the loss caused by the temperature measuring device, and obtain a more accurate total temperature measurement when the influence on the original flow field is as small as possible.

Description

technical field [0001] The invention relates to a rotating mechanical blade suitable for aerospace vehicles. The structure has high accuracy, and the loss caused by the measuring device is small, which has little influence on the efficiency of the whole machine. Background technique [0002] With the increase of energy demand, petroleum, as a non-renewable energy source, is facing resource shortage. Aircraft manufacturers, engine manufacturers and related organizations are actively carrying out efforts to improve fuel efficiency. The measurement accuracy of thermal efficiency will directly affect the calculation of aircraft efficiency, and thermal efficiency is related to the measured total temperature. Therefore, in order to accurately measure the performance and efficiency of a spacecraft, we must measure the total temperature and total pressure in the engine. At present, the general measurement method is to install a temperature probe at the axial or circumferential posi...

Claims

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Application Information

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IPC IPC(8): G01K7/22G01K7/06G01K1/20
CPCG01K7/22G01K7/06G01K1/20
Inventor 崔佳欢刘俭王稳
Owner ZHEJIANG UNIV
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