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Total temperature and total pressure wing-shaped sensing part

An airfoil and airfoil technology, which is applied in the field of aerodynamic parameter testing of aeroengines, can solve problems such as the influence of the flow field quality of cylindrical struts, and achieve the effects of ensuring strength, preventing flow leakage loss, and reducing additional weight

Active Publication Date: 2014-09-10
AECC SHENYANG ENGINE RES INST
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

In the past, the test structure, such as the invention with the patent number Zl201120299935.6, either did not combine multiple testing functions, or the invention with the patent number Zl201110000317.1 met the requirements of multiple functions, but the flow field quality was not affected by the wake of the cylindrical strut. brought new influence

Method used

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  • Total temperature and total pressure wing-shaped sensing part
  • Total temperature and total pressure wing-shaped sensing part
  • Total temperature and total pressure wing-shaped sensing part

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Embodiment Construction

[0027] Such as figure 1 , figure 2 As shown, the total temperature and total pressure wing-shaped sensing part of the present invention is designed as two parts: a temperature measuring rod and a wing-shaped housing. The main components include: a temperature-measuring rod 1, a wing-shaped housing 2, a metal conduit 3 and a flange . The air flow into the wing-shaped shell is divided into two paths, one path passes through the square air intake hole 5 and the exhaust hole 6, and exchanges heat with the hollow stepped cylinder. The resistance value of the built-in temperature sensitive element Pt100 platinum resistance changes with the temperature of the incoming flow , the temperature value is calculated by the follow-up measurement circuit; the other way enters the bottom through hole 9, through The metal conduit 3 leads to the pressure joint 11, and the pressure joint 11 is connected with a pressure sensor or a pressure scanning valve with a pre-connected pipeline to obta...

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Abstract

The invention discloses a total temperature and total pressure wing-shaped sensing part, and belongs to the technical field of testing of aerodynamic parameters of an aero-engine. The total temperature and total pressure wing-shaped sensing part is characterized by comprising a temperature measuring rod, a wing-shaped shell body, a metal conduit and a flange, wherein the temperature measuring rod and a wing-shaped shell are fastened by the flange, inserted into a testing hole of an engine case, and sealed in a vibration attenuation manner by a copper pad. A platinum resistor precise thermo-sensitive element is arranged in the terminal end of the temperature measuring rod to sense and measure a temperature of an airflow which is delayed by air inlet and air outlet of the wing-shaped shell, and a total pressure of a flow field is extracted from a semispherical hole in the bottom of the shell. Compared with former pneumatic gauging structures, the total temperature and total pressure wing-shaped sensing part has the advantages of small flow resistance and high intensity, avoids turbulence of a uniform flow field of an engine inlet and the like caused by testing structural members; meanwhile, the total temperature and total pressure parameters are measured integrally, so that the mounting number of the testing structural members is reduced, the weight is lightened, and flow loss caused by flow damage ratio, leakage and the like is reduced.

Description

technical field [0001] The invention belongs to the technical field of testing aerodynamic parameters of aero-engines, and in particular designs a total temperature and pressure wing-shaped sensing part for testing aerodynamic parameters of a uniform flow field section such as an engine or a gas turbine inlet. Background technique [0002] The research and development of aeroengines and gas turbines is inseparable from repeated ground engineering verification. During the test, a series of aerodynamic parameters need to be measured. Key input parameters such as the total temperature and total pressure of the engine inlet are particularly important for the test safety and performance evaluation of the engine. In the past, the test structure, such as the invention with the patent number Zl201120299935.6, either did not combine multiple testing functions, or the invention with the patent number Zl201110000317.1 met the requirements of multiple functions, but the flow field qualit...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M15/02G01M15/14
Inventor 袁帅孙琪王晓良刘忠奎刘岩
Owner AECC SHENYANG ENGINE RES INST
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