IVENS DANIEL HOFFMANN; DMITRY SUSLOV; JAN DEEKEN; JUSTIN HARDI

DOI Number: 10.13009/EUCASS2023-032

The performance and stability of liquid rocket engines heavily rely on the behavior of the injector. Achiev­ing an effective chemical reaction and highly efficient homogeneous fuel mixture within a minimal cham­ber length is a major challenge. This requirement extends to various modem combustion systems such as chemical industrial plants, heating systems, and engines, placing extreme demands on injection equipment. This article presents a concept for a Swirler injector for the oxidizer that utilizes helical swirlers with different angles, lengths, and positions within the injector. The design of this system draws on the DLR Lampoldshausen’s expertise in porous injection technologies, with potential future applications in the DLR LUMEN Technology Demonstrator. To evaluate the performance of the system, tests were conducted at the Water Test Laboratory at DLR Lampoldshausen using water as a simulation of liquid oxygen (LOX) behavior at various pressures (rang­ing from Oto 20 bar). High-speed cameras (Chronos CR21-l.0-16C) were employed for shadowgraphy imaging to visualize the spray angle at the injector post orifice and study atomization. Pressure mea­surements were taken using static pressure sensors at the LOX-Dome and directly before the swirler to assess the influence of pressure loss caused by the swirler in relation to the raw surface condition of the 3D-printed injector. The helical swirlers were differentiated based on the swirler angle (15, 30, and 45 degrees), swirler length (full tum/ 360 degrees or half tum/ 180 degrees), and swirler position (entry, middle, and exit) within the injector.

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In Categories: 1. Aerospace Europe Conference 2023, 1.Events, 10. Propulsion Physics
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