Power plants – Reaction motor – Liquid oxidizer
Patent
1995-01-05
1997-02-18
Freay, Charles G.
Power plants
Reaction motor
Liquid oxidizer
239424, F02K 900
Patent
active
056032137
DESCRIPTION:
BRIEF SUMMARY
The present invention relates to an injector with concentric slits, as well as to the associated injection elements, this injector being intended to be used in rocket engine combustion units such as the propulsion chamber itself or the combustion chambers of gas generators.
BACKGROUND OF THE INVENTION
The injector is a part which comprises one or more injection elements allowing the combustion unit to be fed with the propellant(s) necessary for its operation, such that there is rapid and complete mixing of these propellants so as to ensure stable and homogeneous combustion.
In the case of engines using cryogenic propellants, it is customary to employ injectors using injection elements with coaxial jets. However, such an injection system is not suited to all operating conditions, and in particular, it rapidly exceeds its limits and gives unsatisfactory results when high performance is demanded as regards the injection of very high propellant flowrates. With such a system, it is therefore not possible to expect significant cost savings.
By contrast, the injector geometry described in the NASA report "Noncircular orifices holes and advanced fabrication techniques for liquid rocket injectors", published in the journal: NASA CR 134315 MAY 1974, allows operation at high flowrates to be envisaged, the different injection elements having a structure with rectangular slits, the performance and characteristics of which are independent of the injected flowrate. Nevertheless, the geometry is not entirely satisfactory because it is not simple to produce, the integration of the elements into an injector being particularly complex, and moreover, the performance which results is greatly reduced by incomplete mixing at the ends of that slit due to the presence at that location of an excess of hydrogen relative to oxygen.
Patent U.S. Pat. No. 3,446,024 seeks to suppress this end effect by producing an injector with an injection element which is circular rather than rectilinear. However, the geometry disclosed in that document restricts possibilities of arranging a plurality of injection elements at a single injector, and the way in which propellants are fed to the different sheets does not guarantee identical flowrates for the propellants, i.e. quality flows and therefore good combustion.
OBJECTS AND SUMMARY OF THE INVENTION
An object of the present invention is to alleviate the drawbacks in the prior art by using a new injector architecture with parallel sheets which ensures high performance even at very high flowrates. Another object of the invention is to propose a simple injector with a particularly small number of component parts, thereby reducing production costs compared with those of the prior art. A further object of the invention is to obtain a reliable injector without the risk of creating fluid losses which give rise to undesired mixing of the propellants or cause hot spots from which deterioration within the combustion chamber originates.
These objects are achieved by a parallel sheet injector provided with a body about an axis to which there is coaxially connected at least one annular injection element comprising a central annular injection slit surrounded by two other annular injection slits, wherein said central annular slit is fed with a second propellant which enters at the top of the injection element level with said central slit and wherein said other annular slits are fed with a first propellant which enters at the base of the injection element, on either side of the central slit, and passes through an annular homogenization cavity from which it flow towards the annular slits surrounding the central injection slit.
The injection element is fed with the first propellant from a central cavity and from at least one other annular cavity arranged at the inlet and at the base of said injection element and fed from bores arranged parallel to the axis and extending, from a propellant feed cavity, into one or more concentric annuluses. Likewise, this injection element is fed with the second propellant from
REFERENCES:
patent: 3050262 (1962-08-01), Curtis
patent: 3085393 (1963-04-01), Hamlin et al.
patent: 3242670 (1966-03-01), Buswell
patent: 3446024 (1969-05-01), Lewis et al.
patent: 3780952 (1973-12-01), Huang
patent: 4722181 (1988-02-01), Yu
Beaurain Andre
Desclos Pierre
Sion Martin
Freay Charles G.
Societe Europeenne de Propulsion
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