# The Effect of Blade Angle Deviation on Mixed Inflow Turbine Performances
###### Abstract
[10; 11] mentioned that the VGT (variable geometry turbine) is the next step in turbo compression technology at this time, and they conducted a series of VGT-equipped engine tests and examined the improvement achieved. They found that an \"ideal\" nozzle, specially designed for mixed-flow rotor entry, is essential for obtaining the maximum VGT performance. [PERSON] et al. [12] used a pivoting nozzle vane to control the inlet mixed flow turbine. The recent development of VGT was experimentally tested by [PERSON] et al. [13], which was designed to match the 3D of the mixed-flow turbine geometry at the leading edge. The design and the experimental data obtained by [PERSON] [14] are used for validation throughout the current research. [PERSON] et al. [15] investigated stator end wall designs numerically for a mixed flow turbine. [PERSON] et al. [16] designed and analyzed the volute of a radial and a mixed flow turbine. [PERSON] et al. [17] numerically studied a mixed flow turbine volute operating in various steady flow conditions. [PERSON] et al. [18] presented the influence of volute cross-section shape on mixed inflow turbine performances. [PERSON] et al. [19] analyzed the impact of a volute aspect ratio on the performance of a mixed flow turbine performance. [PERSON] et al. [20] investigated a twin entry flow turbine volute and benefits concerning the eco-system. [PERSON] et al. [21] studied the inlet mixed inflow turbine geometry. [PERSON] and [PERSON] [22] studied the volute to rotor interspace loss on mixed turbine performance. Some researchers were interested in the operating conditions of mixed inflow turbines: [PERSON] [23] and [PERSON] [24; 25; 26] modified the mechanism of actuation of sliding vanes to adapt to the nature of the pulsating flow of exhaust gas by inducing artificially sinusoidal motion. [PERSON] and [PERSON] [27] reported the earliest experimental study of the irregular flow effect on mixed inflow turbine performance. [PERSON] et al. [3] analyzed four rotors of inflow mixed turbines with different camber curves. [PERSON] et al. [28] studied the effects of flow conditions at rotor inlet on mixed flow turbine performance for automotive applications. In work [29], the unsteady rotor flow-field timescale in a highly loaded mixed flow turbine using validated 3-D unsteady computational fluid dynamics (CFD) carried out by ANSYS-CFX was quantitatively investigated. In paper [30], to control the shock wave and to improve the flow conditions of highly-loaded turbine cascades, an inverse method study on the S1 stream surface was conducted to weaken shock wave strength using the blade profile at the mid-span of the second stage rotor blade of an E3 turbine. [PERSON] and [PERSON] [31] concluded that the mixed inflow turbine design could be optimized by adjusting the volute outlet vortex angle to zero or a certain positive value. [PERSON] al. [32] numerically and experimentally studied the flow angle effect on mixed inflow turbine performance and discovered that only one rotor blade part operates in optimal conditions. [PERSON] et al. [33] studied the constant blade angle effect on the mixed inflow turbine performance in the steady and in the unsteady state. Given the fact that the rotor shape has great importance, as it is the main element for the transformation of kinetic energy into mechanical energy, much attention has also been paid to this issue in modern literature. [PERSON] et al. [34] obtained the rotor geometry of the mixed flow turbine by radially scanning the leading edge of a radial turbine. This modification resulted in a blade curvature reduction of the secondary flow concerning its radial counterpart. [PERSON] et al. [35] established a relationship between the blade angle, the cone angle, and the camber angle. [PERSON] et al. [36] studied the effect of blade number on mixed inflow turbine performances. [PERSON] [37] presented mixed flow turbine rotor design and performance analysis with extended blade chords. [PERSON] et al.