Aerodynamic development and investigation of turbine transonic rotor blade cascades

Mayorskiy, E. V.; Mamaev, B. I.

doi:10.1134/s0040601515050080

Cited by 6 publications

(2 citation statements)

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“…where m≈1 for modern aerodynamically efficient profiles, which means that the outlet flow angle is equal to the gauge angle, cos À1 (O/S). 22 In order to accurately calculate the deviation angle of transonic flow, Mamaev 23,24 proposed a model for the flow velocity at λ 2 ≈0.9-1.1. This model is complicated and uses the theorem of angular momentum and control volume analysis at the throat and cascade outlet.…”

Section: Empirical Modelsmentioning

confidence: 99%

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One dimensional approach to predict the performance of high pressure multi-stage axial turbine considering air cooling and diffuser performance

Zhang,

Yang

2023

Proceedings of the Institution of Mechanical Engineers, Part A:

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This paper provides an improved 1D mid-span program to quickly grasp the off-design characteristic of modern axial turbines. The improvements are mainly focused on cooling, diffuser and the calculation of choke condition. Disk cooling and blade cooling air mixing are considered in detail. A 1D diffuser model that considers the effects of area change, heat transfer, and friction is added so that a realistic boundary condition at the turbine outlet can be obtained. A choke routine that enables the assessment of choked flow up to limit load conditions is introduced to avoid the shortcoming that the calculation method fails to converge near or at the initial choking mass flow rate. Flexible modules for losses, deviation, and mixing models are built-in to increase the accuracy and versatility of the program. This work is of great value because few programs take cooling and diffuser into account in such detail when calculating turbine performance in the form of maps. The salient issues presented here deal first with the construction of the turbine performance prediction program. The validation of the code is first performed on public data for a five-stage low pressure turbine (LPT). The results show that the efficiency relative errors with the experimental value is in the range of −(0.11%−1.64%), which is within acceptable limits. Then, the performance of GE PG9351FA transonic axial turbine is estimated using this program. This industrial axial turbine is predicted for the first time in a form of turbine performance maps in open literature and the obtained performance map is very useful for the simulation of gas turbine.

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Section: Empirical Modelsmentioning

confidence: 99%

“…In order to accurately calculate the deviation angle of transonic flow, Mamaev 23,24 proposed a model for the flow velocity at λ2 ≈0.9–1.1. This model is complicated and uses the theorem of angular momentum and control volume analysis at the throat and cascade outlet.…”

Section: One-dimensional Modelingmentioning

confidence: 99%

One dimensional approach to predict the performance of high pressure multi-stage axial turbine considering air cooling and diffuser performance

Zhang,

Yang

2023

Proceedings of the Institution of Mechanical Engineers, Part A:

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Uncertainty quantification of geometric variations in transonic high-pressure turbine with different trailing edge and throat area distribution

Chen,

Zou,

Yao

et al. 2024

Aerospace Science and Technology

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An Aerodynamic Investigation of the Last-Stage Turbine in an Upgraded Gas Turbine

Liu,

Pan,

Liu

et al. 2024

Journal of Fluids Engineering

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Due to the lengthy certification process for newly designed turbine blades, product upgrading of industrial gas turbine units is often performed solely on compressor and combustor. Since their inlet conditions are significantly changed, the entire four-stage turbine operates far away from its original design point, leading to decreased efficiency and increased flutter risk. This investigation firstly performs numerical simulations to study the flow field change of the last-stage turbine in a gas turbine before and after product upgrading. To reduce the load of the last-stage turbine without reducing the power output of the whole turbine, the enthalpy drops of turbine is reallocated to the front three stages. After modifying the blade profile based on S1 stream surface analysis, a CFD simulation is carried out on the modified three-dimensional blade passage. It is shown that the modified blade design greatly reduces the Mach number at the tip outlet of the last-stage blade, thus possibly reducing flutter risk and improving the aerodynamic efficiency of the turbine. This paper also attempts to redesign the blade geometry by different radial blade stacking of both forward sweep and backward sweep. It is found that the backward-swept blade modification can effectively reduce the endwall flow loss. This work presents the improvements of the aerodynamic efficiency of last-stage through a series of improvement methods and provides a reference for future detailed optimization of this last-stage turbine.

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Aerodynamic development and investigation of turbine transonic rotor blade cascades

Cited by 6 publications

References 0 publications

One dimensional approach to predict the performance of high pressure multi-stage axial turbine considering air cooling and diffuser performance

One dimensional approach to predict the performance of high pressure multi-stage axial turbine considering air cooling and diffuser performance

Uncertainty quantification of geometric variations in transonic high-pressure turbine with different trailing edge and throat area distribution

An Aerodynamic Investigation of the Last-Stage Turbine in an Upgraded Gas Turbine

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