NOVEL INJECTOR DESIGN FOR HYBRID ROCKET ENGINE

Abstract

This invention provides an improved injector design for hybrid rocket engines, featuring a two-stage buffer zone and an injector plate with angled holes for enhanced fuel atomization and stable combustion. The design improves thrust efficiency, minimizes pressure fluctuations, and promotes complete combustion within the chamber, making it ideal for high-performance rocket applications.

Specification

Description:FIELD OF THE INVENTION
This invention relates to aerospace engineering and rocket propulsion technology, focusing on a novel injector design for hybrid rocket engines. The design introduces a two-stage buffer zone and an improved injector plate with multiple angled holes, enhancing fuel atomization, combustion stability, and overall engine efficiency in hybrid rockets.
BACKGROUND OF THE INVENTION
Hybrid rocket engines, which combine liquid oxidizers and solid fuels, rely heavily on efficient fuel injection to achieve stable and complete combustion. Conventional injector systems often face issues with inconsistent mass flow rates and pressure drops, leading to unstable combustion and reduced engine performance. Variations in pressure or flow can lead to non-uniform fuel-oxidizer mixing, which disrupts the combustion process and affects thrust generation. This invention addresses these challenges by introducing an injector with a two-stage buffer zone to maintain consistent pressure and an injector plate designed with multiple holes at a specific angle, ensuring even distribution and atomization of fuel. The design aims to improve fuel-oxidizer mixing, reduce instability in combustion, and increase thrust efficiency, providing an optimized solution for hybrid rocket engines.
SUMMARY OF THE INVENTION
This summary is provided to introduce a selection of concepts, in a simplified format, that are further described in the detailed description of the invention.
This summary is neither intended to identify key or essential inventive concepts of the invention and nor is it intended for determining the scope of the invention.
To further clarify advantages and features of the present invention, a more particular description of the invention will be rendered by reference to specific embodiments thereof, which is illustrated in the appended drawings. It is appreciated that these drawings depict only typical embodiments of the invention and are therefore not to be considered limiting of its scope. The invention will be described and explained with additional specificity and detail with the accompanying drawings.
The invention provides a novel injector design featuring a two-stage buffer zone and an enhanced injector plate configuration for hybrid rocket engines. The two-stage buffer zone stabilizes the fuel delivery pressure, while the injector plate incorporates multiple holes at a 20-degree angle, improving fuel atomization and mixing within the combustion chamber. The design increases combustion efficiency, minimizes pressure drops, and enhances engine stability, making it suitable for use in high-performance hybrid rockets. The injector components are constructed from materials like stainless steel and composites for durability and reliability under extreme conditions.
BRIEF DESCRIPTION OF THE DRAWINGS
The illustrated embodiments of the subject matter will be understood by reference to the drawings, wherein like parts are designated by like numerals throughout. The following description is intended only by way of example, and simply illustrates certain selected embodiments of devices, systems, and methods that are consistent with the subject matter as claimed herein, wherein:
FIGURE 1: SHOWS THE SIDE VIEW OF THE INJECTOR DESIGN, HIGHLIGHTING THE BUFFER ZONES AND OVERALL STRUCTURE.
FIGURE 2: PRESENTS THE FRONT VIEW OF THE INJECTOR, DISPLAYING THE ARRANGEMENT OF THE HOLES ON THE INJECTOR PLATE.
FIGURE 3: ILLUSTRATES THE SECTIONAL VIEW OF THE INJECTOR, INDICATING THE FLOW DIRECTION OF THE PROPELLANT WITHIN THE BUFFER ZONES.
The figures depict embodiments of the present subject matter for the purposes of illustration only. A person skilled in the art will easily recognize from the following description that alternative embodiments of the structures and methods illustrated herein may be employed without departing from the principles of the disclosure described herein.
DETAILED DESCRIPTION OF THE INVENTION
The detailed description of various exemplary embodiments of the disclosure is described herein with reference to the accompanying drawings. It should be noted that the embodiments are described herein in such details as to clearly communicate the disclosure. However, the amount of details provided herein is not intended to limit the anticipated variations of embodiments; on the contrary, the intention is to cover all modifications, equivalents, and alternatives falling within the scope of the present disclosure as defined by the appended claims.
It is also to be understood that various arrangements may be devised that, although not explicitly described or shown herein, embody the principles of the present disclosure. Moreover, all statements herein reciting principles, aspects, and embodiments of the present disclosure, as well as specific examples, are intended to encompass equivalents thereof.
The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of example embodiments. As used herein, the singular forms "a"," "an" and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise. It will be further understood that the terms "comprises," "comprising," "includes" and/or "including," when used herein, specify the presence of stated features, integers, steps, operations, elements and/or components, but do not preclude the presence or addition of one or more other features, integers, steps, operations, elements, components and/or groups thereof.
It should also be noted that in some alternative implementations, the functions/acts noted may occur out of the order noted in the figures. For example, two figures shown in succession may, in fact, be executed concurrently or may sometimes be executed in the reverse order, depending upon the functionality/acts involved.
In addition, the descriptions of "first", "second", "third", and the like in the present invention are used for the purpose of description only, and are not to be construed as indicating or implying their relative importance or implicitly indicating the number of technical features indicated. Thus, features defining "first" and "second" may include at least one of the features, either explicitly or implicitly.
Unless otherwise defined, all terms (including technical and scientific terms) used herein have the same meaning as commonly understood by one of ordinary skill in the art to which example embodiments belong. It will be further understood that terms, e.g., those defined in commonly used dictionaries, should be interpreted as having a meaning that is consistent with their meaning in the context of the relevant art and will not be interpreted in an idealized or overly formal sense unless expressly so defined herein.
The novel injector design for hybrid rocket engines introduced here comprises a multi-component structure focused on improving fuel atomization, pressure consistency, and combustion stability. The injector assembly consists of two primary zones: the two-stage buffer zone (Zone-A) and the injector plate zone (Zone-B). The buffer zones are critical in stabilizing the pressure within the fuel delivery system, ensuring a steady and controlled fuel flow into the combustion chamber.
The two-stage buffer zone includes an initial cavity to regulate fuel pressure as it enters the injector. This buffer zone minimizes fluctuations in fuel pressure, preventing sudden drops or spikes that could disrupt combustion. The steady pressure provided by the buffer zone ensures consistent fuel delivery, improving the reliability and performance of the hybrid rocket engine. The controlled environment within the buffer zones reduces risks of irregular combustion, enabling smoother and more uniform fuel burning.
The injector plate is designed with eight holes, each angled at 20 degrees to enhance fuel atomization and distribution within the combustion chamber. The holes are evenly spaced in a circular pattern around the injector plate, providing a uniform spray of fuel into the chamber. The angled holes help direct the fuel flow towards the center, ensuring effective mixing with the oxidizer. This configuration increases the contact area between the fuel and oxidizer, promoting complete combustion and optimizing thrust production. The improved fuel atomization achieved by the injector plate design leads to more efficient burning of the fuel, maximizing energy output and reducing waste.
Constructed from materials such as stainless steel 302, stainless steel 208, and composite materials, the injector is designed to withstand the extreme conditions within a rocket engine. The choice of materials ensures durability and corrosion resistance, allowing the injector to maintain its structural integrity and performance over extended use. The two-stage buffer zone and the advanced injector plate configuration collectively enhance the stability, efficiency, and reliability of hybrid rocket engines, making this design a valuable innovation in aerospace propulsion technology.
, Claims:1. An injector design for hybrid rocket engines comprising a two-stage buffer zone and an injector plate with angled holes, enabling consistent fuel pressure and enhanced atomization for improved combustion.
2. The injector design as claimed in Claim 1, wherein the two-stage buffer zone stabilizes fuel pressure, reducing fluctuations in the fuel delivery system and supporting stable combustion.
3. The injector design as claimed in Claim 1, wherein the injector plate includes eight holes positioned at a 20-degree angle, providing even fuel distribution and optimized mixing with the oxidizer.
4. The injector design as claimed in Claim 1, wherein the angled holes on the injector plate increase the contact area between fuel and oxidizer, promoting complete combustion and improving thrust efficiency.
5. The injector design as claimed in Claim 1, wherein the injector components are constructed from stainless steel and composite materials, ensuring durability and corrosion resistance under high-temperature conditions.
6. A method for enhancing fuel atomization as claimed in Claim 1, involving the use of a two-stage buffer zone and an angled-hole injector plate to regulate fuel pressure and improve combustion stability.
7. The injector design as claimed in Claim 1, wherein the two-stage buffer zone and angled-hole injector plate collectively reduce combustion instability, ensuring uniform burning of the propellant and consistent engine performance.

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