Accession Number:

AD1101522

Title:

Detonation Confinement in a Radial Rotating Detonation Engine

Descriptive Note:

Technical Report,01 Oct 2018,01 Mar 2020

Corporate Author:

AIR FORCE INSTITUTE OF TECHNOLOGY WRIGHT-PATTERSON AFB OH WRIGHT-PATTERSON AFB United States

Personal Author(s):

Report Date:

2020-03-26

Pagination or Media Count:

194.0

Abstract:

Radial Rotating Detonation Engines RRDE have provided an opportunity for use of a pressure-gain combustor in a more compact form compared to an axial RDE. A successfully tested RRDE was modified from its constant area detonation chamber to a decreasing area design as the flow travelled radially inward to confine the detonation wave to a more radially outward position to improve combustion time and efficiency. The detonation chamber featured a flat channel plate that reduced the flows effective crosssectional area by almost 65 from its inlet to the turbine inlet plane. The constant channel height improved total pressure loss as high as 92 over the constant area geometry for similar flow conditions and increased the RRDEs ability to operate at larger channel heights. Guide vanes were introduced downstream of the combustion section by modifying the flat channel plate with modular channel plates. While in this configuration, the RRDE operated at both detonative and acoustic wave modes. Thin-filament pyrometry TFP was also performed to measure transient temperature responses during operation. The successful implementation of the filaments provided temperature measurements during detonative modes up to 2194 K at the guide vanes and frequency responses captured through TFP between 1.6-5.9 kHz

Subject Categories:

  • Combustion and Ignition

Distribution Statement:

APPROVED FOR PUBLIC RELEASE