A compressor stator blade with a large bending angle and a multi-section blade type connected in series at the root

Abstract

The invention discloses a large bending angle air compressor stator blade serially connected with multiple sections of blade shapes at root part. The stator blade comprises hub end walls, chassis end walls and a stator blade, wherein the stator blade is formed by showing direction smooth connection of curvature continuous chassis side serial small blades with a stator blade body and the chassis end walls and showing direction smooth connection with curvature continuous hub side serial small blades with the stator blade body and the hub end walls; and the chassis side serial small blades and the hub side serial small blades have different blade shape geometries. Under the working conditions of different incoming currents, self-pressure-difference jet currents from gaps of serial small blades at the root part of the stator blade can be effectively acted on low-energy fluids in end areas of the stator blade, and carry the same to develop at the downstream to reconstruct end area flowing fields, so that the three-dimensional angular area separation / stall caused by accumulation of low-energy fluid groups in the end area of the stator blade under large bending angle is inhibited, the circulating capacity of a stator blade channel is improved, the effective working and working condition range of an air compressor stator is widened, and the performances under different working conditions are improved.

Description

technical field [0001] The invention relates to a compressor stator blade design scheme for suppressing separation of three-dimensional angular regions of a compressor stator blade, in particular to a compressor stator blade with a large bending angle whose roots are connected in series with multiple blade shapes, and belongs to the passive flow control technology in the technical field of turbomachinery. Background technique [0002] The compressor is the core component of the aviation gas turbine engine. It is composed of multi-stage rotors and stators arranged in a staggered order, and its function is to increase the gas pressure rise. [0003] In the flow inside the compressor, the secondary flow in the blade and end wall corner area caused by the large reverse pressure gradient is an inherent and complex flow phenomenon, so the loss is the main source of loss in the flow inside the compressor; three-dimensional The flow congestion caused by corner separation / stall makes...

AI Technical Summary

Problems solved by technology

[0004] After decades of research, many scientific researchers have gained a deep understanding of the flow mechanism in the three-dimensional corner area of ​​the compressor. However, due to the complexity of its flow structure, as well as the limitations and reliability of experimental measurements and numerical simulations, At present, the accurate prediction and reliable control of the three-dimensional corner separation flow of the compressor have not been well realized according to the existing mechanical research results; the research on the three-dimensional corner separation flow mechanism, flow prediction and flow control of the compressor is always a high-performance Key Issues Concerned in Compressor Design

[0005] At present, the flow control technologies for the three-dimensional angular separation and stall of compressor stator blades can be divided into two categories: active control technology and passive control technology in terms of whether additional energy is introduced: active control technologies mainly include plasma excitation, boundary surface Layer blowing and suction technology, synthetic jet, etc.; passive control technology mainly includes vortex generators, wing blades, end wall molding, etc.; active control technology has a wide range of applications and obvious benefits, but it requires additional energy and is not easy to implement in engineering; the existing Traditional passive control technology is not self-adaptive, and the range of effective working conditions is often limited, which fails to solve the problem of corner separation of the next generation of high-load compressors in engineering

Images