Power plants – Reaction motor – Liquid oxidizer
Reexamination Certificate
1999-09-08
2001-06-12
Freay, Charles G. (Department: 3746)
Power plants
Reaction motor
Liquid oxidizer
Reexamination Certificate
active
06244040
ABSTRACT:
FIELD OF THE INVENTION
The invention relates to the field of power machine-building and concerns the Fulfillment of gas generators for driving gas turbines in particular for liquid-propellant rocket engines.
BACKGROUND OF THE INVENTION
A gas generator for a liquid-propellant rocket engine is known that comprises a spherical structural envelope, an outlet pipe rigidly fastened to it, propellant and oxidizer inlet pipes and an injector face, in which injectors are coaxially installed (U.S. Pat. No.4,974,415, 1990).
In the known construction it is difficult to ensure high-quality mixing and a stable combustion process at high ratio of the oxidizer flow rate to the propellant flow rate with compactness of the whole unit.
The solution most similar to the present invention is a gas generator comprising a structural envelope with an outlet pipe, a cylindrical combustion chamber located in the structural envelope, a cover stationarily fastened on the structural envelope, an injector face located in the structural envelope, mixing modules provided with a housing with a propellant passage, an annular oxidizer passage and a mixing chamber, the housing fixed in the injector face and inlet pipes for feeding the propellant and oxidizer which are connected respectively propellant passages and oxidizer passages of the mixing modules (U.S. Pat. No. 5,339,635, 1994).
In the known gas generator it is impossible to produce generator gas with a heightened amount of oxidizer therein that is necessary for the operation in liquid-propellant rocket engines using oxygen.
SUMMARY OF THE INVENTION
The object of the present invention is to enhance the reliability and operating efficiency of gas generators for liquid-propellant rocket engines.
The technical result which may be attained where the present invention is carried out is an improvement of the mixing the quality combustible mixture and stability of its combustion when liquid oxygen and kerosene are used as the main propellant components.
The essence of the invention is that a gas generator for liquid-propellant rocket engines comprises a structural envelope an outlet pipe rigidly fastened to the structural envelope, a cover having a bush made on the inner surface thereof and rigidly connected to the said structural envelope from the side opposite to the outlet pipe, an injector face with through chambers, which is stationarily mounted in a bush to form a space between the injector face and the cover, a spacer mounted inside the structural envelope to form an annular space between them and fastened at one end to the outlet pipe and at another end outer surface of the bush and a combustion chamber envelope disposed inside the spacer and the outlet pipe. Mixing modules, are positioned in the space between the cover and the injector face, each of the modules has a housing with a propellant passage an annular oxidizer passage and a mixing chamber located coaxially therein the housing fastened in the cover from the propellant passage side, and from the mixing chamber side in the injector face chamber. A propellant feed inlet pipe is fixed in the cover to form a propellant space and an oxidizer feed inlet pipe is fixed in the middle part of the structural envelope and communicates with its annular space, The annular space of the structural envelope communicates with the space between the cover and the injector face through ports made in the bush, the propellant passage of each mixing module is connected to the propellant space by calibrated openings made in the cover, the space between the cover and the injector face communicates with the annular oxidizer passages of the mixing modules through the openings made in the housing of the mixing module and is hydraulically connected to the chamber in the injector face.
A cover may be provided with an insert positioned in the propellant space, wherein the space between the cover and the injector face to the chambers may be made in the form of slots positioned on the external surface of the part of housing to which the mixing modules are attached, in an injector face calibrated openings are made, in the insert, and the hydraulic coupling of the combustion. The injector face chambers may be provided with tapered bores made from the side of chamber, wherein the tapered surfaces of the bores of adjacent chambers are made intersecting.
The combustion chamber envelope may be installed in a spacer and outlet pipe to form a cooling space there between communicating with the annular space of the structural envelope. The structural envelope may be made spherical, the outlet pipe may be tapered and connected to the structural envelope by its wide end, and the combustion chamber envelope wherewith is made with cylindrical and tapered sections.
REFERENCES:
patent: 3712059 (1973-01-01), Drezhage
patent: 4974415 (1990-12-01), Shekleton et al.
patent: 5339635 (1994-08-01), Iwai et al.
patent: 5660039 (1997-08-01), Sion et al.
patent: 6112515 (2000-09-01), Klotz et al.
Adzhian Alexei Pogosovich
Bogushev Vladimir Jurievich
Katorgin Boris Ivanovich
Kolesnikova Valentina Dmitrievna
Samsonov Alexandr Mikhailovich
Christie Parker & Hale LLP
Freay Charles G.
Otkrytoe Aktsionernoe Obschestvo "Nauchno-Proizvodstvennoe Obied
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