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research-article

T63 TURBINE RESPONSE TO ROTATING DETONATION COMBUSTOR EXHAUST FLOW

[+] Author and Article Information
Andrew G. Naples

ASME Member, Innovative Scientific Solutions Incorporated
anaples@gmail.com

John Hoke

ASME Member, Innovative Scientific Solutions Incorporated
johnhoke@hotmail.com

Ryan Battelle

ASME Member, US Air Force
bridgewaterfoundry@gmail.com

Fred Schauer

ASME Member, US Air Force
an7mal@gmail.com

1Corresponding author.

ASME doi:10.1115/1.4041135 History: Received July 02, 2018; Revised July 18, 2018

Abstract

This paper describes testing an axial turbine response when driven by a Rotating Detonation Combustor (RDC). A T63 (C20-250) gas turbine is modified by replacing the combustor with a RDC. The stator vanes of the T63 are heavily instrumented for measurement of flow enthalpy and pressure. The engine is run at multiple power levels with the stock combustor using JetA and hydrogen fuel. The engine is then modified to have an open loop configuration, and is run with both the RDC and the stock combustor hardware with hydrogen fuel. Temperature pattern factor, flow unsteadiness, and turbine component efficiency are measured for all setups. High speed pressure transducers show substantially higher unsteadiness generated by the RDC than the conventional combustor. RDC turbine component efficiencies are compared to the conventional combustor. Results suggest that RDC unsteadiness does not significantly impact turbine efficiency.

Section 4: U.S. Gov Employees + Reg Authors
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