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Research Papers

T63 Turbine Response to Rotating Detonation Combustor Exhaust Flow

[+] Author and Article Information
Andrew Naples, John Hoke

Mem. ASME
Innovative Scientific Solutions Incorporated,
Dayton, OH 45459

Ryan Battelle, Fred Schauer

Mem. ASME
U.S. Air Force,
WPAFB, OH 45433

Manuscript received July 2, 2018; final manuscript received July 18, 2018; published online October 16, 2018. Editor: Jerzy T. Sawicki. This work is in part a work of the U.S. Government. ASME disclaims all interest in the U.S. Government's contributions.

J. Eng. Gas Turbines Power 141(2), 021029 (Oct 16, 2018) (8 pages) Paper No: GTP-18-1424; doi: 10.1115/1.4041135 History: Received July 02, 2018; Revised July 18, 2018

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 the 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.

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Figures

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Fig. 1

Simplified T63 gas turbine engine cross section [24]

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Fig. 2

Flow schematic for typical “closed-loop” T63 gas turbine

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Fig. 3

Flow schematic for the “open-loop” RDC testing

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Fig. 4

Cross section of the detonation channel with exhaust dilution section

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Fig. 5

Cross section of the complete T63 RDC

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Fig. 6

Basic instrumentation map for T63 testing

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Fig. 7

Picture of instrumented, first stage, T63 nozzle guide vane set

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Fig. 8

Picture of instrumented, third stage, T63 nozzle guide vane set

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Fig. 9

Combustor outlet and chemical equilibrium analysis combustor exhaust stagnation temperature differential for all tests, at all power levels

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Fig. 10

Compressor and output shaft power variation with time for a typical T63 test

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Fig. 11

ITP measurement upstream and downstream of HPT for the RDC and conventional turbine tests

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Fig. 12

Unsteadiness factor upstream and downstream of the HPT and detonation wave passing frequency for the RDC test

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Fig. 13

Temporally averaged combustor pattern factor as a function of combustor outlet enthalpy flux for all test points

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Fig. 14

Turbine map showing points from all tests

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