NTRS - NASA Technical Reports Server

Advisory – Planned Maintenance: On Monday, July 15 at 9 PM Eastern the STI Compliance and Distribution Services will be performing planned maintenance on the STI Repository (NTRS) for approximately one hour. During this time users will not be able to access the STI Repository (NTRS).

Back to Results
Effect of Detonation through a Turbine StagePulse detonation engines (PDE) have been investigated as a more efficient means of propulsion due to its constant volume combustion rather than the more often used constant pressure combustion of other propulsion systems. It has been proposed that a hybrid PDE-gas turbine engine would be a feasible means of improving the efficiency of the typical constant pressure combustion gas turbine cycle. In this proposed system, multiple pulse detonation tubes would replace the conventional combustor. Also, some of the compressor stages may be removed due to the pressure rise gained across the detonation wave. The benefits of higher thermal efficiency and reduced compressor size may come at a cost. The first question that arises is the unsteadiness in the flow created by the pulse detonation tubes. A constant pressure combustor has the advantage of supplying a steady and large mass flow rate. The use of the pulse detonation tubes will create an unsteady mass flow which will have currently unknown effects on the turbine located downstream of the combustor. Using multiple pulse detonation tubes will hopefully improve the unsteadiness. The interaction between the turbine and the shock waves exiting the tubes will also have an unknown effect. Noise levels are also a concern with this hybrid system. These unknown effects are being investigated using TURBO, an unsteady turbomachinery flow simulation code developed at Mississippi State University. A baseline case corresponding to a system using a constant pressure combustor with the same mass flow rate achieved with the pulse detonation hybrid system will be investigated first.
Document ID
Acquisition Source
Document Type
Ellis, Matthew T.
(Purdue Univ. IN, United States)
Date Acquired
August 23, 2013
Publication Date
January 1, 2004
Publication Information
Publication: Research Symposium I
Subject Category
Aircraft Propulsion And Power
Distribution Limits
Work of the US Gov. Public Use Permitted.

Available Downloads

There are no available downloads for this record.
No Preview Available