Design and evaluation of high performance rocket engine injectors for use with hydrocarbon fuels

The feasibility of using a heavy hydrocarbon fuel as a rocket propellant is examined. A method of predicting performance of a heavy hydrocarbon in terms of vaporization effectiveness is described and compared to other fuels and to experimental test results. Experiments were done at a chamber pressure of 4137 KN/sq M (600 psia) with RP-1, JP-10, and liquefied natural gas as fuels, and liquid oxygen as the oxidizer. Combustion length effects were explored over a range of 21.6 cm (8 1/2 in) to 55.9 cm (22 in). Four injector types were tested, each over a range of mixture ratios. Further configuration modifications were obtained by reaming each injector several times to provide test data over a range of injector pressure drop

A resonance-tube igniter for hydrogen-oxygen rocket engines

Resonance-tube igniter for hydrogen-oxygen rocket engine

Advanced tube-bundle rocket thrust chamber

An advanced rocket thrust chamber for future space application is described along with an improved method of fabrication. Potential benefits of the concept are improved cyclic life, reusability, and performance. Performance improvements are anticipated because of the enhanced heat transfer into the coolant which will enable higher chamber pressure in expander cycle engines. Cyclic life, reusability and reliability improvements are anticipated because of the enhanced structural compliance inherent in the construction. The method of construction involves the forming of the combustion chamber with a tube-bundle of high conductivity copper or copper alloy tubes, and the bonding of these tubes by an electroforming operation. Further, the method of fabrication reduces chamber complexity by incorporating manifolds, jackets, and structural stiffeners while having the potential for thrust chamber cost and weight reduction

Resonance tube igniter

Reasonance induced in stoichiometric mixtures of gaseous hydrogen-oxygen produces temperatures /over 1100 deg F/ high enough to cause ignition. Resonance tube phenomenon occurs when high pressure gas is forced through sonic or supersonic nozzle into short cavity. Various applications for the phenomenon are discussed

Detection of beet soil-borne virus and beet virus Q in sugarbeet in Greece

Sugar beet plants with typical rhizomania symptoms were collected from the five major cultivation zones of Greece. The presence of Beet necrotic yellow vein virus (BNYVV), the primary causal agent of the disease, was ascertained by DAS-ELISA in 38 out of 40 fields surveyed and the positive samples were subsequently examined for the presence of other soil-borne viruses which are frequently associated with rhizomania, using a multiplex RT-PCR assay targeting BNYVV, Beet soilborne virus (BSBV) and Beet virus Q (BVQ). The occurrence of BSBV and BVQ was confirmed in 9 and 23 rhizomania-infected fields, respectively. In contrast to surveys conducted in other countries, the presence of BVQ prevailed throughout Greece in dual infections with BNYVV, whereas BSBV was restricted to rhizomania-infected fields from only two sugarbeet cultivation areas. Nine of the samples tested were infected with all three viruses. BSBV was always found in triple infections. To our knowledge, this is the first report of BSBV and BVQ in Greece. The future assessment of the impact of each of these viruses on sugarbeet could prove significant for bleeding objectives in terms of achieving a more durable resistance to the rhizomania syndrome

Efficiency of Rz-1 based rhizomania resistance and molecular studies on BNYVV isolates from sugar beet cultivation in Geece

A survey was carried out to investigate the current situation concerning rhizomania disease incidence in sugar beet cultivation of Greece. A systematic field evaluation over locations and years revealed a consistent disease severity pattern according to favourable agroclimatic conditions and pointed to the so far effectiveness of the Rz1 gene-based resistance, as no major disease outbreaks were observed. Molecular analyses aiming at the characterization of the type and genetic diversity of the virus further confirmed the widespread occurrence of BNYVV in the country, as evidenced by RT-PCR amplification of all five known genomic molecules and nested-PCR assays. None of the isolates contained an RNA 5, typically found in pathotype P. On the basis of RFLP patterns, all BNYVV isolates analysed were classified as pathotype A. Sequence determination of the full-length RNA 3-encoded p25 protein, responsible for symptom development, revealed amino acid motifs ACHG/VCHG in the hypervariable region aa67–70. The presence of valine in position 67 did not appear associated with increased pathogenicity and resistance breaking properties, as earlier reported

Hot fire fatigue testing results for the compliant combustion chamber

A hydrogen-oxygen subscale rocket combustion chamber was designed incorporating an advanced design concept to reduce strain and increase life. The design permits unrestrained thermal expansion of a circumferential direction and, thereby, provides structural compliance during the thermal cycling of hot-fire testing. The chamber was built and test fired at a chamber pressure of 4137 kN/sq m (600 psia) and a hydrogen-oxygen mixture ratio of 6.0. Compared with a conventional milled-channel configuration, the new structurally compliant chamber had a 134 or 287 percent increase in fatigue life, depending on the life predicted for the conventional configuration

New method of making advanced tube-bundle rocket thrust chambers

An improved method of fabrication rocket chambers for future space applications is described. Included are fabrication demonstrator and test chambers produced by this method. This concept offers the promise of improved cyclic life, reusability, and performance. The performance is improved because of the enhanced enthalpy extraction. The improved cyclic life, reusability, and reliability is improved because of the structural compliance inherent in the construction. The method of construction involves the forming of the combustion chamber by a tube-bundle of high conductivity copper or copper alloy tubes and the bonding of these tubes by a unique electroforming operation. Furthermore, the method of fabrication reduces chamber complexity by incorporating manifolds, and structural stiffeners while having the potential for thrust chamber cost and weight reduction

Experimental and theoretical investigation of fatigue life in reusable rocket thrust chambers

During a test program to investigate low-cycle thermal fatigue, 13 rocket combustion chambers were fabricated and cyclically test fired to failure. Six oxygen-free, high-conductivity (OFHC) copper and seven Amzirc chambers were tested. The failures in the OFHC copper chambers were not typical fatigue failures but are described as creep rupture enhanced by ratcheting. The coolant channels bulged toward the chamber centerline, resulting in progressive thinning of the wall during each cycle. The failures in the Amzirc alloy chambers were caused by low-cycle thermal fatigue. The zirconium in this alloy was not evenly distributed in the chamber materials. The life that was achieved was nominally the same as would have been predicted from OFHC copper isothermal test data