Liquid Hydrogen and the SABRE Engine

Alan Bond Founder & Chief Engineer

R E A C T I O N E N G I N E S L T D Slide 1 SKYLON’S PURPOSE

“The SKYLON launch system has the primary purpose to achieve the lowest cost access to space possible with both current technology and commercial feasibility.”

THE SKYLON SPACEPLANE 5 SKYLON’S MISSION PROFILE

THE SKYLON SPACEPLANE 5 Origins of LH2 Rocket Fuel in the UK

DeHaviland proposal 1960 by Denis Hurden

Proposals for practical work by:- Rolls- Royce APR/R4 Aug 1963 (heavily dependent on RPE work) Bristol Siddeley RR 76 29 July 1963 (domestic facility using Screamer components)

R E A C T I O N E N G I N E S L T D Slide 4 Insert Title Here RPE Westcott Lox/LH2 20kN Chamber (1962) Built by BAJ Banwell

R E A C T I O N E N G I N E S L T D Slide 5 RPE chamber on A site

R E A C T I O N E N G I N E S L T D Slide 6 The R-R 70kN Engine RZ20 Rolls-Royce very sensibly built heavily on the Wescott experience.

They moved to vacuum furnace brazing instead of hand layup as was still used on the RZ2 and was very expensive.

Pressurised thin stainless steel ‘baloons’ were used to hold the tubes and braze alloy in place during brazing

R E A C T I O N E N G I N E S L T D Slide 7 Back to A Site Westcott

R E A C T I O N E N G I N E S L T D Slide 8 R-R liquid hydrogen test stand at Spadeadam

Built with Company investment

Pressure fed facility (700psi)

Liquid hydrogen supplied by RPE Westcott and tanked to Spadeadam

R E A C T I O N E N G I N E S L T D Slide 9 RZ20 Test 1 8 September 1969 20sec

R E A C T I O N E N G I N E S L T D Slide 10 RZ20 post test hardware

Shell burn-through

R E A C T I O N E N G I N E S L T D Slide 11 collapsed dip pipe from hydrogen tank

R E A C T I O N E N G I N E S L T D Slide 12 R E A C T I O N E N G I N E S L T D Slide 13 R E A C T I O N E N G I N E S L T D Slide 14 Precooler

Compressor

Turbine Air Intake

Bypass Duct

Thrust Chambers

R E A C T I O N E N G I N E S L T D Slide 15 PRE-COOLER HEAT EXCHANGER

THE SKYLON SPACEPLANE 5 LOX cooling Test bench P8, Lampoldshausen Germany

R E A C T I O N E N G I N E S L T D Slide 17 DLR Film Cooling Test Facility at P8 Lampoldshausen measurement segment nozzle supply line GH2

supply film injector

R E A C T I O N E N G I N E S L T D Slide 18 Strict Engine – first test firing June 2011

R E A C T I O N E N G I N E S L T D Slide 19 The Phase 3 Objectives (36 month Programme)

• Raise engine technology to TRL 6 through ground testing. • Complete the design of the SABRE4 to manufacturing drawings. • Ensure that the vehicle requirements and SABRE4 engine design are compatible. • Flight test the nacelle design (desirable).

R E A C T I O N E N G I N E S L T D Slide 20 The B9 Area, Culham Science Centre

R E A C T I O N E N G I N E S L T D Slide 21 D1 requirements are now established and validated.

Configuration revision proceeds: a fully trimmed solution has been found, but it will require further study before it can be finalised.

External contributions to D1 design (expand available skill base):

- Aerodyanmic modelling - Structure loads analysis - Payload interface - Avionics and electrical power

R E A C T I O N E N G I N E S L T D Slide 22 Length ≈ 9m Span ≈ 3.5m Mass ≈ 1000kg

R E A C T I O N E N G I N E S L T D Slide 23 Thank you!

Visit reactionengines.co.uk

R E A C T I O N E N G I N E S L T D Slide 24