A compressor test platform was designed in the purpose of easy assembly and cost-saving tests.New design concepts were firstly used on the test platform and iterative revisions were conducted to verify the effects,whi...A compressor test platform was designed in the purpose of easy assembly and cost-saving tests.New design concepts were firstly used on the test platform and iterative revisions were conducted to verify the effects,which decrease the risk of applying to the full annulus directly.The platform was a sector cascade that can be inserted into an otherwise full stator annulus,with a set of exchangeable endwall casing and blades manufactured by 3-D printing.The platform can create an operating condition which is closer to engine-realistic flow conditions than traditional cascade tests.The flow field of the prototype stator was tested in detail at the operating point and showed some flow defects in the tip region,and then three design plans were conducted to experimentally investigate which design concept could improve the blade tip flow.The concept of casing endwall profiling was the most effective one which markedly depressed the separation of the tip region and decreased the total pressure loss coefficient.The test results show that the design of the test platform was successful and promising,which could be used to conduct more researches on the flow mechanism of the middle stage.展开更多
Due to corner separation and other complex three-dimensional flows existing in the highly loaded stator, which influences the fan performance significantly, highly loaded stator blades of a transonic fan with a maximu...Due to corner separation and other complex three-dimensional flows existing in the highly loaded stator, which influences the fan performance significantly, highly loaded stator blades of a transonic fan with a maximum camber angle of 57° were studied in this paper and sector cascade experiment was adopted. In order to get the stator aerodynamic parameters as realistic as possible and conduct the experiment without the existence of rotor, an adjustable guide vane was designed to simulate the velocity magnitude and direction of the stator inlet flow. Results show that the adjustable guide vane can simulate the rotor outlet velocity direction and magnitude in most span range. The deviation angle is positive and the maximum value is nearly 21° because the severe separation is at 27% span. Corner separation exists on both pressure side and suction side and the location of separation initiation is determined. Finally, the stator blades were redesigned with some suction slots on the suction side. Experiment results show that the suction slots change the flow field structure, increase the capability of flow turning, and decrease the flow loss.展开更多
基金supported by the National Science and Technology Major Project(2017-Ⅱ-0004-0017)。
文摘A compressor test platform was designed in the purpose of easy assembly and cost-saving tests.New design concepts were firstly used on the test platform and iterative revisions were conducted to verify the effects,which decrease the risk of applying to the full annulus directly.The platform was a sector cascade that can be inserted into an otherwise full stator annulus,with a set of exchangeable endwall casing and blades manufactured by 3-D printing.The platform can create an operating condition which is closer to engine-realistic flow conditions than traditional cascade tests.The flow field of the prototype stator was tested in detail at the operating point and showed some flow defects in the tip region,and then three design plans were conducted to experimentally investigate which design concept could improve the blade tip flow.The concept of casing endwall profiling was the most effective one which markedly depressed the separation of the tip region and decreased the total pressure loss coefficient.The test results show that the design of the test platform was successful and promising,which could be used to conduct more researches on the flow mechanism of the middle stage.
基金funded by the National Natural Science Foundation of China (51576024, 51436002)the Program for Liaoning innovative Research Team in University (LT2015004)
文摘Due to corner separation and other complex three-dimensional flows existing in the highly loaded stator, which influences the fan performance significantly, highly loaded stator blades of a transonic fan with a maximum camber angle of 57° were studied in this paper and sector cascade experiment was adopted. In order to get the stator aerodynamic parameters as realistic as possible and conduct the experiment without the existence of rotor, an adjustable guide vane was designed to simulate the velocity magnitude and direction of the stator inlet flow. Results show that the adjustable guide vane can simulate the rotor outlet velocity direction and magnitude in most span range. The deviation angle is positive and the maximum value is nearly 21° because the severe separation is at 27% span. Corner separation exists on both pressure side and suction side and the location of separation initiation is determined. Finally, the stator blades were redesigned with some suction slots on the suction side. Experiment results show that the suction slots change the flow field structure, increase the capability of flow turning, and decrease the flow loss.
