Turbine blade cooling effect test system and method
A technology of turbine blade and cooling effect, which is applied in the field of turbine blade cooling effect test system, can solve the problem that it is difficult to meet the requirements of high-efficiency turbine blade cooling test, and cannot meet the accuracy requirements of blade cooling design and heat transfer analysis. Due to the complexity of blade cooling design technology and other problems, it can achieve the effect of not being limited by location, low test cost, and flexible in use.
Pending Publication Date: 2022-08-05
SHANGHAI POWER EQUIP RES INST
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Problems solved by technology
The cooling design technology of high-efficiency turbine blades is becoming more and more complex. Simply relying on design experience or numerical calculations cannot meet the accuracy requirements of blade cooling design and heat transfer analysis. The turbine blade cooling effect test must be carried out, and the shape can only be finalized after passing the test verification
However, the gas turbine blade cooling effect test device in the related art has been difficult to meet the high-efficiency turbine blade cooling test requirements as the inlet temperature of the turbine blade continues to increase.
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[0019] The following describes in detail the embodiments of the present invention, examples of which are illustrated in the accompanying drawings. The embodiments described below with reference to the accompanying drawings are exemplary, and are intended to explain the present invention and should not be construed as limiting the present invention.
[0020] According to the turbine blade cooling effect test system according to the embodiment of the present invention, the turbine blade cooling effect test system includes a static turbine blade cooling test device 7 , an aeroengine 1 , a cooling air source device 8 , a test cooling water device 9 , and a control system 10 and the data acquisition system 11, the static turbine blade cooling test device 7 is used to test the stationary turbine blades and the static turbine moving blades, the gas generator 6 of the aero-engine 1 includes a main flow gas for supplying the static turbine blade cooling test device 7 The combustion cha...
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The invention discloses a turbine blade cooling effect test system and method, and the system comprises a static turbine blade cooling test device, an aero-engine, a cooling air source device, a test cooling water device, a control system, and a data collection system. The static turbine blade cooling test device is used for testing a turbine stator blade and a static turbine rotor blade, the fuel gas generator comprises a combustion chamber and a gas compressor, and the cooling gas source device is used for controlling the flow and pressure of cooling air entering the turbine blade cooling test device. The test cooling water device is used for cooling exhaust pipeline shell sides of an inlet and an outlet of the static turbine blade cooling test device, the control system is used for controlling the output quantity of mainstream fuel gas, cooling air and cooling water, and the data acquisition system is used for acquiring operating parameters of the test system and sending the operating parameters to the control system. The turbine blade cooling effect test system provided by the invention has the advantages that the test cost is low, the test device is not limited by the position, and the use is flexible.
Description
technical field [0001] The invention relates to the technical field of gas turbines, in particular to a system and method for testing the cooling effect of turbine blades. Background technique [0002] In order to improve market competitiveness, gas turbines need to continuously improve the output and efficiency of the unit, resulting in the continuous increase of the inlet temperature of the turbine blades. In order to ensure the safe, stable and long-life operation of turbine blades at higher temperatures, in addition to using more advanced materials, it is more important to introduce high-efficiency turbine blade cooling design technology. The cooling design technology of high-efficiency turbine blades is becoming more and more complex, and the accuracy requirements of blade cooling design and heat transfer analysis cannot be met simply by design experience or numerical calculation. The cooling effect test of the turbine blade must be carried out, and the shape can be fi...
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IPC IPC(8): G01M15/14G01M15/02G01M13/00
CPCG01M15/14G01M15/02G01M13/00
Inventor谢岳生刘网扣张成义史进渊王建业张琳
OwnerSHANGHAI POWER EQUIP RES INST