LT6464B - Spacecraft engine fuel spray-valve with a heat control system - Google Patents

Abstract

Invention relates to the design of a spacecraft engine fuel spray-valve with a heat control system. The spray-valve consists of: a valve controller for moving the valve to open and close the fuel inlet to the combustion chamber; a valve closing / opening said opening; a housing connecting all parts of the spray-valve to the whole and having an O-shaped sealing ring, a protective filter and other function elements; a heat control system consisting of a heat transfer element and a thermal barrier to ensure the proper temperature of the fuel supply system and the fuel contained therein and the protection against overheating. The essence of the invention is by this technical solution eliminating the pipeline between the fuel supply control valve and the combustion chamber, ensuring precise and uniform pressure (during the entire specific pulse) fuel supply to the combustion chamber. This increases the engine's handling and fuel efficiency. The sprayer is easy to integrate into spacecraft engines.

Description

TECHNICAL FIELD

The present invention relates to the field of aerospace engines, and more particularly to aerospace engine fuel injector and valve and heat transfer designs.

TECHNICAL LEVEL

This description provides a technical solution that improves the efficiency of spacecraft engines, improves their controllability and uses fuel more efficiently. The essence of the technical solution is to eliminate the fuel flow pipeline between the fuel flow control valve and the combustion chamber. The fuel supply system described in the description requires a specific heat management system to prevent the fuel from exploding without reaching the combustion chamber.

Patent document US7757476B2 (published July 20, 2010) provides a somewhat schematic solution, but the essence of the cited patent is different from that of the present invention. Although the fuel inlet valve is shown schematically next to the combustion chamber, the exact position of the valve and the related technical functions cannot be judged from the drawing alone, and no explanation is given in the description itself. Also, the cited document does not mention the problem of direct fuel supply or its solutions. The recirculating cooling system disclosed in the cited document is essentially unsuitable for the present invention due to the possibility of too little heat (power) being removed.

US4326377A, issued April 27, 1982, provides a technical solution that is somewhat similar in design to the one described herein, but which introduces a function of forming the pressure required to supply fuel. There is no mention of direct injection of fuel into the combustion chamber. Thus, although this design may be regarded as the closest analog to the present invention, its purpose is to provide fuel pressure rather than direct fuel delivery. The document thus quoted solves a completely different problem that is not related to direct fuel supply, eliminating unnecessary piping. The design principles of the quoted technical solution are more suitable for high power engines, as well as complex design.

The above analogs have the following disadvantages:

- it is clear from the construction and description that the above analogues do not solve the problem of direct fueling which determines engine efficiency;

- the cooling systems provided are not structurally capable of providing sufficient cooling;

- Analog solutions are narrowly applicable and not suitable for other engine designs.

The following technical solution in this description does not have the disadvantages listed above.

THE SUBSTANCE OF THE INVENTION

The essence of the invention is that this technical solution, by eliminating the pipeline between the fuel supply control valve and the combustion chamber, ensures accurate, uniform pressure (throughout the specific impulse) supply of fuel to the combustion chamber. This results in increased engine control as well as improved fuel efficiency. Sprayer-valve is easy to integrate with spacecraft engines.

The present invention relates to the construction of a fuel injector valve for aero-engines with a heat control system. This design includes:

a valve controller for moving the valve to open and close the fuel inlet to the combustion chamber;

a valve closing and opening said aperture;

a housing integrating all parts of the sprayer-valve assembly and having an 'O' or other form of sealing ring, protective filter and other functions;

wherein the heat management system is comprised of a heat transfer element and a thermal barrier to provide an appropriate temperature for the fuel feed system and the fuel contained therein to protect it (system) from overheating.

BRIEF DESCRIPTION OF THE DRAWINGS

Fig. 1 shows a longitudinal cross-section of a spray-valve with a combustion chamber.

PREFERRED EMBODIMENTS

Space vehicles (hereinafter referred to as "spacecraft") use jet engines. Formerly and now widely used in aerospace engine fuels such as ammonium perchlorate (AP) and / or hydrazine (eng: hydrazine). This fuel is toxic and harmful to the environment and also requires sophisticated equipment to properly fit in spacecraft. One of the most researched and best spacecraft substitutes for this type of fuel is the one-component fuel developed and refined on the basis of ammonium dinitramide (ADN). ADN fuel does not have the disadvantages of previous fuel and is also more energy efficient, but it has different physical and chemical properties, which makes the equipment used and the operating principles of the previous fuel unsuitable for ADN fueled engines.

Some of the parameters that determine the performance of a spacecraft engine are the duration of the specific pulse and the steepness of the pulse fronts. The lower the pulse duration, the greater the traction control of the engine. Another parameter that affects efficiency and is dependent on the minimum pulse duration is the pulse front staticity (front length), a parameter measured in time units. The shorter the time it takes the pulse to reach its target state (value) from its initial state, the more efficient the motor is. At the start of a pulse, this is the time from the lowest (zero) value of the pulse to the highest value; and at the end of the pulse, it is the time from highest to lowest.

One of the technical solutions proposed by the present invention reduces the length of the fronts. The reduction in duration is achieved by eliminating the pipeline between the valve controlling the fuel feed and the combustion chamber, i.e., the fuel supply control valve opens and closes the orifice located in the wall of the combustion chamber itself.

This description describes a unit that integrates a sprinkler, valve, heat management system and other elements. The entirety of these integrated elements will be referred to hereinafter as the "spray-valve". The terms "sprayer" or "valve", when used separately, mean separate parts of the sprayer-valve: the sprayer or valve, respectively.

Removal of the said fuel flow pipeline between the supply control valve and the combustion chamber must ensure proper cooling of the fuel supply system. A new technical solution to this is the system for controlling excess heat in said valve. Because the temperature of the ADN fuel in the combustion chamber is significantly higher (up to + 1600 ° C) than conventional fuels, a proper heat transfer system from the fuel is required, given the fact that the fuel inlet valve operates adjacent to the combustion chamber feed valve and other fuel feed elements. Without proper heat dissipation, ADN fuel that reaches a certain temperature (~ 90 ° C) can explode without reaching the combustion chamber, i.e. the fuel system, thus damaging the injector valve or engine.

The engine component of the present invention disclosed herein can be conditionally divided into at least two components: a valve injector and a combustion chamber. The spray-valve part is connected to the combustion chamber. The present invention provides a combustion chamber which is no different from those used at present, so that the following description will be limited to what is necessary to illustrate the invention. If following the direction of fuel flow, the injector-valve is connected to the combustion chamber in the opening (end of the fuel flow channel), which is closed or opened by a needle valve. This description describes a device for controlling the amount of fuel supplied to the combustion chamber (valve) and the fuel pressure generating equipment is no different from the state of the art.

The said spray valve shall comprise at least the following components:

- Needle valve actuator (actuator) (1);

- Needle valve (valve) (2);

- Sprayer-valve housing (housing) (3);

- a protective filter (4);

- a heat transfer element (5);

- thermal barrier (6).

Needle valve (2) control (1) for moving the needle valve (2) to open and close the hole in the valve (2). In one embodiment, the needle valve (2) is pushed by a spring (or similar function) element toward the opening of the fuel outlet to the combustion chamber (7), so that normally the needle valve (2) keeps the opening closed. The said controller (1) generates a mechanical force which, upon overcoming the spring resistance, moves the needle valve (2) and opens the fuel flow port. The controller (1) is connected to the valve (2) in such a way that it is capable of transmitting the motive force. The controller (1) may be an electromagnetically driven electromagnetic coil that converts electrical energy into magnetic energy that moves the valve (2). Thus, the controller (1) may not have direct contact of the material with the valve (2). When using an electromagnetic coil, it surrounds one end of the valve (2), i.e., the valve (2) is inside the coil. In another embodiment, the controller (1) may operate on a piezoelectric basis, wherein the piezoelectric, when exposed to electricity, generates a mechanical force that moves the valve (2). The use of piezoelectric to move the valve (2) results in a significantly higher movement speed, shorter transients, and more accurate positioning of the valve (2).

The shape of the needle valve (2) resembles an elongated rod having a cylindrical (or other similar) shaped element at one end, which allows the solenoid coil to have better contact with the valve (2). If other means of moving the valve (2) are used, said end of the valve (2) may be of a different shape to properly engage the control (1). In another embodiment, the valve (2) may be made of a solid material. The valve (2) is made of chemically resistant magnetic (this feature is relevant if the controller is electromagnetic) stainless steel. The key requirement for the valve (2) material is chemical compatibility with the fuel. As mentioned, one end of the valve (2) is connected (or actuated) to the valve (2) control (1), and the other end of the elongated rod of the valve (2) closes the opening through which fuel may flow into the combustion chamber (7). Said opening is located in the wall of the combustion chamber (2), i.e. the valve (2) is adjacent to the wall of the combustion chamber (7) when closing said opening. The end of the valve (2) which closes the orifice is tapered, i.e. is similar to the geometric shape of the cone. In other embodiments, the tip of the cone of the valve (2) may be cut off, i.e., the end of the valve (2) resembles the shape of a cut cone. A portion of the elongated rod of the valve (2) is inserted into the fuel flow pipe. Said pipe may be a separate element to be clamped (or fixed to the pipe) mentioned above: spray gun body (3), heat transfer element (5), thermal barrier (6) and other elements. In another embodiment, said tube is formed by a spray gun body (3), a heat transfer element (5), a thermal barrier (6) and other elements.

Sprayer body (3) connects all sprayer elements and combustion chamber (7). A controller (1) is attached to one end of the housing (3). An oblong portion of the valve (2) extends through the housing (3). Said pipe, which holds the elongated part of the valve (2), has an "O" sealing ring which touches the housing (3) on its outer walls and the elongated part of the valve (2) is pierced through an inner hole. The "O" ring prevents the fuel from flowing in the opposite direction to the combustion chamber (7).

Before entering the said pipe, which has a valve (2), the fuel flows through a protective filter (4) in the housing (3) which retains the fuel impurities. The housing (3) may contain other structural elements which perform various functions, but they do not affect the present invention. The case (3) may be made of various metal alloys capable of losing their properties at high temperatures or in a chemically aggressive environment, for example: SS316, SS317 and / or other similar metal alloys may be used.

Behind the housing (3), in the direction of the flow of fuel, there is a heat transfer element (5). The basic requirement for the material of the heat transfer element (5) is high thermal conductivity (low thermal resistance). The heat transfer element (5) may also perform the function of a nozzle-valve fastener, in which case the material from which the heat transfer element (5) is made must be mechanically rigid to properly attach the nozzle-valve. In the case of the present invention, the heat transfer element (5) is made of copper or alloys in which copper is the major component. Depending on the various functions of the heat transfer element (5), this element may take various forms depending on the constructional features of the other elements. The elements to which the heat transfer element is attached may contribute to faster heat transfer from the sprayer if their temperature is lower than that of the sprayer and if they are made of heat-conductive material. The heat transfer element (5) hugs and / or surrounds the fuel flow pipe, so that part of the element is designed to absorb heat dissipated. Further, due to the high thermal conductivity, the heat transfer element (5) transmits the absorbed heat to its entire housing, which transfers heat to the environment and / or to the elements to which the heat transfer element (5) is attached. In other embodiments, an additional cooler, such as an element operating on the Peltje principle or otherwise, may be used.

Another element in the direction of fuel flow is the thermal barrier (6). The main function of the thermal barrier (6) is to prevent the propagation of heat from the fuel combustion chamber (7) to the injector and to the fuel supply system upstream of the fuel flow. The thermal barrier (6) encloses / hugs the pipe through which the fuel flows. The thermal barrier (6) resembles a tube of circular cross-section with a thin wall. In the case of the present invention, the surface of the outer wall of the tube resembles a repeating "W" shape, i.e., the plane forming the surface is an angular waveform, where the wave edges extend parallel to the longitudinal axis of the tube. Such a surface is formed to extend the heat transfer path (or increase the resistivity) and to increase the surface area of the outer surface to improve heat transfer (cooling) properties. The outer surface of the thermal barrier (6) may also have other shapes and materials. Basic requirements for barrier (6) material: heat and chemical resistance; the material must also have a low thermal conductivity (high thermal resistance). Ceramics, low thermal conductivity metal, various composite materials can be used.

The heat dissipation element (5), the thermal barrier (6) and the electric heater form the nozzle-valve heat control system. The purpose of the thermal barrier (6) is to prevent the propagation of heat against the direction of fuel flow, the heat transfer element (5) ensuring that the remaining heat of the thermal barrier (6) is conducted outwards. An electric heating element ensures that the fuel feed system does not cool down below the crystallization temperature of the fuel. The thermal barrier (6) partially functions as a heat insulator, and the heat dissipation element (5) ensures proper heat dissipation, i.e. cooling of the fuel supply system. In the case of the present invention, the LMP-103S fuel has a combustion chamber temperature of + 1600 ° C and a fuel explosion temperature of ~ 90 ° C. An additional safety margin of 10 ° C is used to ensure that the fuel system and fuel do not reach temperatures above 80 ° C. In the present invention, the heat management system is selected and adapted to provide the above-described temperature regime. The heat transfer system chosen is an integral part of the invention due to the low explosion temperature of the fuel (relative to the combustion temperature in the combustion chamber) and the peculiarities of the flow of the fuel through a spray valve.

As mentioned, the fuel is fed to the injector through a protective filter (4) in the housing (3). The required fuel pressure is provided by equipment not mentioned in this description. Behind the protective filter (4), the fuel enters the pipe, which flows to the opening of the fuel outlet to the combustion chamber (7). The O-ring seal prevents fuel from flowing in the direction opposite to the hole in the fuel outlet (7). In said pipe, which feeds the fuel towards the combustion chamber (7), there is an elongated part of the valve (2). As the fuel flows towards the combustion chamber (7), there is a heat transfer element (5) behind the housing (3) and a thermal barrier (6) behind it. The heat dissipation element (5) and the thermal barrier (6) are part of a jet-valve heat control system that provides the necessary fuel temperature to the combustion chamber (7) and prevents overheating that may cause the fuel to explode before reaching the combustion chamber (7). ). The fuel flow pipe ends in a hole in the wall of the combustion chamber (7). Before the opening of the pipe narrows, the form of the narrowing must accurately reproduce the shape of the end of the valve (2) so that the valve (2), together with the pipe narrowing, forms a tight contact with the flowing fuel when closing the opening. This valve (2) design puts the fuel into the combustion chamber under equal pressure at the start and end of the pulse, thereby increasing fuel efficiency.

In order to illustrate and describe the present invention, the following is a description of the most preferred embodiments. It is not a detailed or restrictive description intended to determine the exact form or embodiment. The description above should be viewed as an illustration rather than a limitation. Obviously, many modifications and variations may be apparent to those skilled in the art. An embodiment is selected and described so that those skilled in the art will best understand the principles of the invention and their best practical application for different embodiments with different modifications suitable for a particular application or application. The scope of the invention is intended to be defined by the appended definition and its equivalents, in which all the foregoing terms have the widest possible meaning, unless otherwise stated.

Embodiments described by those skilled in the art may be made without departing from the scope of the present invention as defined in the following definition.

Claims (4)

DEFINITION OF INVENTION A spaceship engine fuel injector valve comprising: a valve actuator (1) which actuates a valve (2); a sprayer body (3) connecting the sprayer and valve elements to a single unit; a heat control system for ensuring proper control of the jet-valve thermal energy, a valve (2) which closes and opens the opening through which the fuel enters the combustion chamber (7), characterized in that the opening through which the fuel enters the combustion chamber (7) ), which is closed and opened by the valve (2), is located on the wall of the combustion chamber (7) adjacent to the combustion chamber (7). 2. A spaceship engine fuel injector valve according to claim 1, characterized in that the heat control system comprises at least: a heat transfer element (5), a thermal barrier (6) and an electric heater. Spacecraft engine fuel injector-valve according to the preceding claims, characterized in that the thermal barrier (6) surrounds the pipe for supplying fuel to the combustion chamber closest to the combustion chamber, where the thermal barrier (6) abuts the combustion chamber (7). A spacecraft engine fuel injector valve according to the preceding claims, characterized in that the heat transfer element (5) is located between the thermal barrier (6) and the injector body (3).