The invention discloses a
combustion chamber and
turbine guider integrated composite flow channel outlet flow
field uniformity evaluation method, and belongs to the technical field of gas
turbine pneumatic design. The method comprises the steps that a geometric model of a
combustion chamber and
turbine guider integrated composite flow channel is built, a
combustion chamber function section and a guider pneumatic section are fused through integral pneumatic modeling to form a
continuous flow channel, a front section adopts a
diffusion structure to form a low-speed combustion area, and a rear section adopts a gradually-shrinking channel to achieve gas accelerated expansion; performing three-dimensional cold-state flow field numerical
simulation by adopting a structured grid division and
delay separation vortex
simulation technology; flow parameters including total pressure, Mach number,
airflow angle and vorticity are extracted from the cross section of a flow channel outlet, conversion from a Cartesian coordinate
system to a polar coordinate
system is carried out, and a uniformly distributed aerodynamic parameter field is reconstructed by using an interpolation
algorithm; the
directional coupling degree is calculated based on the
spatial correlation of the pressure gradient vector and the vorticity vector, and the vortex-pressure
coupling entropy production index representing the overall aerodynamic loss of the flow channel is established in combination with the pressure pulsation intensity and the vorticity
concentration ratio. According to the method, a three-dimensional
evaluation system is constructed by integrating circumferential and radial non-uniformity and
entropy production parameters, and accurate quantitative evaluation of flow characteristics and uniformity of the
combustion chamber and turbine integrated structure is realized.