A Review of Supersonic Turbines Based on Constant Volume Combustion Cycle

Conference paper
Part of the Lecture Notes in Electrical Engineering book series (LNEE, volume 680)


In this paper, in response to the current demand for new aerospace power in the aerospace field, thermodynamic performance and thermal efficiency advantages of existing constant volume combustion cycles are reviewed. The main challenge in the practical implementation of Pressure Gain Combustion (PGC) into gas turbines and aero-engine is the lack of turbomachinery that can efficiently harvest work from the PGC exhaust gas. Therefore, this paper analyzes the supersonic inflow conditions with pressure, temperature and velocity pulsations at the outlet of the detonation combustion chamber, and puts forward the difficulties brought by the inflow conditions to the design of the turbine cascade. Secondly, this paper analyzes the aerodynamic characteristics of turbine cascade passage under supersonic inlet conditions, analyzes the influence of channel shock waves on aerodynamic losses, and expounds the importance of turbine under supersonic inlet conditions in detonation combustion cycle.


Constant volume combustion cycle PGC Detonation combustion inflow condition Supersonic turbine 


List of Symbols


Pressure ratio of compressor [–]


Dimensionless heat absorption [–]


Heat [J]


Density [kg/m3]


Pressure [Pa]


Entropy [J/(mol K)]


Thermal efficiency [–]


Output work [J]


Enthalpy [J/mol]


Specific heat capacity at constant pressure [J/(kg K)]


Specific heat capacity at constant volume [J/(kg K)]


Temperature [K]


Ratio of specific heats [–]


Mach number [–]


Axial velocity [m/s]


Speed of sound [m/s]


Shock angle [°]


Airflow angle [°]


Gas constant [J/(mol K)]


Flange work [J]


Correction coefficient


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Copyright information

© The Author(s), under exclusive license to Springer Nature Singapore Pte Ltd. 2021

Authors and Affiliations

  1. 1.Harbin Institute of TechnologyHarbinChina

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