Studies on the Effect of Staggering the Rear Rotor in a Counter Rotating Turbine with Respect to Flow and Performance Parameters
-
Rayapati Subbarao
and
M. Govardhan
Abstract
Counter rotating turbine is an axial turbine with nozzle followed by a rotor and another rotor that rotates in the opposite direction of the first one. Absence of the second guide vane makes it more beneficial. Present work involves computationally studying the performance and flow pattern of CRT with different stagger angles ranging from 8 to 13° in case of rotor 2. Equivalent mass flow rates of 0.091 to 0.137 are considered. Turbine components nozzle, rotor 1 and rotor 2 are modeled for the cases of CRT with and without staggering. Total pressure, entropy and TKE distributions across the blade rows are used to describe the flow through CRT. Results show that the flow composition at the inlet of rotor 2 is improved for staggering cases. Due to this, the performance of rotor 2 and CRT increased with staggering. For the intermediate mass flow rate of 0.108, the efficiency of CRT stage is found to be increasing by 1.2, 2.1 and 1 % for the staggering cases. The beneficial aspect of staggering the rear rotor is thus confirmed that can provide long-term design solutions in terms of reducing weight, losses and improving the performance.
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© 2019 Walter de Gruyter GmbH, Berlin/Boston
Articles in the same Issue
- Frontmatter
- Original Research Articles
- Optimization Design and Experimental Study of a Two-disk Rotor System Based on Multi-Island Genetic Algorithm
- Experimental Investigation of the Effect of the Probe Support Tail Structure on the Compressor Cascade Flow Field
- Investigation on Rotor-Labyrinth Seal System with Variable Rotating speed
- Numerical Prediction of Impact of Clearance on Rotordynamic Coefficients for Labyrinth Brush Seal
- CH* Luminance Distribution Application and a One-Dimensional Model of the Supersonic Combustor Heat Release Quantization
- Bleeding Control for Improving Internal Waverider Inlet Self-Starting ability
- Soot Formation and Its Effect in an Aero Gas Turbine Combustor
- Studies on the Effect of Staggering the Rear Rotor in a Counter Rotating Turbine with Respect to Flow and Performance Parameters
- Aerodynamic Performance and Flow Characteristics of an Industrial Centrifugal Blower Volute with Varied Cross-Sectional Shapes/Area Ratios
- CFD Design Study of a Pressure Probe for Centerline Static Pressure Measurement in Supersonic Ejectors
- The Performance of the Self-Supplying Vortex Generator Jets on a High-Speed Compressor Cascade
Articles in the same Issue
- Frontmatter
- Original Research Articles
- Optimization Design and Experimental Study of a Two-disk Rotor System Based on Multi-Island Genetic Algorithm
- Experimental Investigation of the Effect of the Probe Support Tail Structure on the Compressor Cascade Flow Field
- Investigation on Rotor-Labyrinth Seal System with Variable Rotating speed
- Numerical Prediction of Impact of Clearance on Rotordynamic Coefficients for Labyrinth Brush Seal
- CH* Luminance Distribution Application and a One-Dimensional Model of the Supersonic Combustor Heat Release Quantization
- Bleeding Control for Improving Internal Waverider Inlet Self-Starting ability
- Soot Formation and Its Effect in an Aero Gas Turbine Combustor
- Studies on the Effect of Staggering the Rear Rotor in a Counter Rotating Turbine with Respect to Flow and Performance Parameters
- Aerodynamic Performance and Flow Characteristics of an Industrial Centrifugal Blower Volute with Varied Cross-Sectional Shapes/Area Ratios
- CFD Design Study of a Pressure Probe for Centerline Static Pressure Measurement in Supersonic Ejectors
- The Performance of the Self-Supplying Vortex Generator Jets on a High-Speed Compressor Cascade
