Abstract
In order to comprehensively control the corner separation and the blade trailing edge (TE) separation in a high-turning compressor stator cascade, this research proposes a new combined slotted configuration consisting of one full-span slot and two blade-end slots. Taking into account the effect of the blade solidity, the performance of the original cascade and the combined slotted cascade was calculated and evaluated in a wide incidence angle range at two blade solidities. The results indicated that the blade loading and the corner separation range of the original cascade becomes larger as the blade solidity decreases from 1.66 to 1.36, which leads to higher total pressure loss and lower pressure diffusing capacity under positive incidence angles. The low-momentum fluid in the boundary layer can be significantly re-energized by the high-momentum blade-end and full-span slots jets, hence the combined slotted configuration can eliminate the blade TE separation and reduce the corner separation remarkably in the full incidence angle range at the two blade solidities. By adopting the combined slotted configuration, the total pressure loss, turning angle and static pressure coefficient of the original cascade can be increased by −23.2%, 2.7° and 4.7% on average, respectively, when the blade solidity is 1.66, while they can be increased by −27.7%, 3.3° and 7.6% on average, respectively, when the blade solidity is 1.36. The combined slotted configuration has a significant adaptability to the low blade solidity (or high loading) condition and it shows a certain potential in increasing the aeroengine thrust-to-weight ratio by decreasing the compressor single-stage blade number.
Highlights
One can see that with the decrease in the blade solidity from 1.66 to 1.36 and the flow separation becomes more serious at 50% H and 5% H under the incidence angle of 6◦, while its degree does not change much under the incidence angle of 0◦
In order to effectively control the trailing edge (TE) separation and corner separation in a high-turning compressor stator cascade, this research proposed a new combined slotted configuration consisting of one full-span slot and two blade-end slots
To investigate the effect of the blade solidity on the combined slotted configuration, the performance of the original cascade and the combined slotted cascade was evaluated in a wide incidence angle range at two blade solidities. the following conclusions can be obtained: 1
Summary
The axial compressor is the core component of aero-engines and it has a great impact on the aero-engines performance [1]. Zhao et al [18] studied the impact of partial clearance on the performance of a 1.5-stage axial compressor, discovering that the stability margin of the compressor can be enlarged in the suitable partial clearance case Other methods such as blade curving [19], nonaxisymmetric EW profiling [20], tandem blades [21], etc., are beneficial for controlling. Under the combined control effect of the vortex generated by the generator and the full-span slot jet, the corner separation was alleviated remarkably and the total pressure loss could be reduced by an average of 30.9%. Afterwards, in order to check the suitability of the combined slotted configuration for higher loading or larger separation conditions, the blade solidity of the original cascade was decreased. The original cascade and the combined slotted cascade were evaluated for aerodynamic performance, in detail, at the two blade solidities
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