Title:
内部ダイバータを有する飛行体エンジンの吸気口、及びその構成方法
Document Type and Number:
Japanese Patent JP6987262
Kind Code:
B2
Abstract:
An inlet for a flight vehicle engine, such as for a supersonic or hypersonic engine, includes an internal flow diverter to divert boundary layer flow. The flow diverter is configured to minimize disruption to flow outside the diverted boundary by being configured through use of a flow field that is also used to configure the walls of the inlet. The flow field that is used to configure an inlet-creating shape and a diverter-creating shape has the same flow generator, contraction ratio, compression ratio, mass capture ratio, pressure ratio between entrance and exit, and/or Mach number, for example. The internal diverter may be configured so as to allow arbitrary selection of a leading edge shape for the internal diverter, for example to use a shape that helps avoid radar detection.
Inventors:
O'Brien, Timothy, F.
Application Number:
JP2020541999A
Publication Date:
December 22, 2021
Filing Date:
May 06, 2019
Export Citation:
Assignee:
RAYTHEON COMPANY
International Classes:
B64D33/02; B64C30/00; F02K1/38
Foreign References:
| US20160376018 |
Attorney, Agent or Firm:
Tadashige Ito
Tadahiko Ito
Osamu Miyazaki
Tadahiko Ito
Osamu Miyazaki