Development of re-usable liquid propulsion rocket engines (LOX / LNG) based on turbo pump fed transpiration cooled, ceramic thrust chambers

Paper number

IAC-19,C4,10,x54410

Year

2019

Abstract

{\bf The development of high performance, but affordable and preferably re-usable propulsion systems is a key component to enable commercial space flight. }

An overview of the technologies under development at Black Engine Aerospace and WEPA-Technologies in collaboration with German Aerospace Center (DLR) will be given and does encompass thrust chambers and turbo pumps.
A turbo pump fed, 60 kN thrust, technology demonstrator (75 bar chamber pressure) using LOX / Liquified Natural Gas (LNG, min. 95 \% methane)  will be presented in detail. 

{\bf - Liquid propellant engines used }are based on transpiration cooled, advanced ceramic thrust chambers. This technology has been thoroughly developed and qualified for example by DLR and shows a high potential of multiple re-usability.  (WEPA in 2016 did receive a license to commercially exploit DLR’s technology.) Due to the segmented design and avoidance of traditional metallic structures manufactured by electrodeposition, fast-track development of  thrust chambers is possible.
The use of LNG – instead of rocket-grade kerosene - as fuel component results in several advantages at the engine- and overall system level crucial to re-usable and lower cost propulsion units:

- increased cooling capability of LNG enabling re-usable thrust chambers

- no deposition of solids caused by cracking of fuel and avoidance of subsequent blocking of cooling channels or turbine blades

- increased overall performance; facilitated design of stage by full cryogenic system (common bulkhead of tanks; less stringent isolation requirements)

{\bf - Turbo pump units using innovative ceramic journal bearings} in order to tackle one of the most demanding issues with respect to their re-usability: while the development of fluid bearings is described in the literature since a long time, the use of ceramic fluid bearings enabling full surface area feed of propellant is innovative and very promising with respect to long life and multiple re-usability of bearings.  (Bearings are being developed in collaboration with DLR and Kaiserslautern University of Technology (Germany)).

The status of design- and experimental activities will be presented.

Abstract document

IAC-19,C4,10,x54410.brief.pdf

Manuscript document

(absent)