Patent Application
20180252115
The embodiments herein generally relate to directed energy weapons and, more particularly, to an electrical power generation system for such weapons, as well as a method of generating electrical power for such weapons.
Directed energy weapons require large amounts of electricity. Due to the desire to place directed energy weapons on airborne platforms, there is a desire to reduce the size of the directed energy weapons systems so they may be placed on smaller aircraft and even space-based platforms. Challenges associated with implementation of directed energy weapons are present in applications that operate at high altitude (e.g., aircraft and spacecraft) based on the need for an electrical power generation system to operate in locations where there is little to no oxygen present. These challenges are unique to applications that are not land-based or on above surface ships, as these applications typically have ample space for large electrical power generation systems and a large supply of oxygen to draw from as an oxidizer that provides the opportunity to liberate energy from an energy storage media, such as jet fuel.
According to one embodiment, an electrical power generation system for a directed energy weapon includes a fuel pump configured to disperse a liquid fuel. Also included is an oxidizer pump configured to disperse a liquid oxidant. Further included is a combustor fluidly coupled to the fuel pump and the oxidizer pump to receive the liquid fuel and the liquid oxidant for combustion therein to form a combustion mixture. Yet further included is a turbine fluidly coupled to the combustor to receive the combustion mixture to generate mechanical energy. Also included is a generator operatively coupled to a rotor shaft of the turbine to convert the mechanical energy to electrical power for the directed energy weapon.
According to another embodiment, a method of generating electrical power for a directed energy weapon is provided. The method includes pumping a liquid fuel to a combustor. The method also includes pumping a liquid oxidant to the combustor for combustion therein to form a combustion mixture. The method further includes routing the combustion mixture to a turbine to convert thermal energy of the combustion mixture to mechanical energy. The method yet further includes converting the mechanical energy to electrical power with a generator operatively coupled to a rotor shaft of the turbine.
The subject matter which is regarded as the disclosure is particularly pointed out and distinctly claimed in the claims at the conclusion of the specification. The foregoing and other features and advantages of the disclosure are apparent from the following detailed description taken in conjunction with the accompanying drawings in which:
Referring to
Although a laser beam 12 is illustrated and referenced herein, it is to be appreciated that the electricity generated by an electrical power generation system 20 (discussed in detail herein) could be used for other directed energy weapons, such as high power microwaves, high power radars, radar jammers, and electromagnetic rail guns.
The directed energy system 10 includes a laser generating assembly located onboard the vehicle 14. The location of the laser generating assembly may vary depending upon the particular embodiment of the vehicle 14. The laser generating assembly includes a plurality of components and subassemblies that in conjunction generate the laser beam 12. Such components relate to power management, weapons targeting, aircraft integration, laser module(s) and thermal cooling, for example. The preceding list is merely illustrative and not intended to be limiting. Irrespective of the precise components of the laser generating assembly, the generated laser beam 12 is routed along a laser carrying component to a laser turret 16 for transmission of the laser beam 12 away from the vehicle 14 to a target. The laser carrying component is operatively coupled to the laser turret 16 and the laser generating assembly. It is to be appreciated that a plurality of laser carrying components may be included to provide multiple laser paths, which may lead to a single laser turret or a plurality of laser turrets.
The directed energy system 10 requires significant power to maintain operation for an extended period of time. As shown in
The electrical power generation system 20 includes a turbine engine 22 that is operatively coupled to a generator 40 in order to generate electrical power to be supplied to the directed energy system 10. The turbine engine 22 includes at least one stage 26 of turbine blades operatively coupled to a turbine rotor 28. The stage 26 of turbine blades are rotated in response to a hot gas combustion mixture that passes over the blades subsequent to combustion in a combustor 30. The combustor 30 is supplied a liquid fuel with a fuel pump 32 and is supplied a liquid oxidant with an oxidizer pump 34. The liquid fuel and the liquid oxidant are mixed within the combustor 30 for combustion therein.
A coolant pump 36 is included in some embodiments to provide a coolant (e.g., water) to the combustor 30 during operation. The coolant pump 36 also provides lubrication and coolant to the rest of the turbine engine 22 and generator 40, as needed. Providing coolant to the combustor 30 reduces the flame temperature within the combustor 30 to reduce the likelihood of damage to turbine components, such as the turbine blades. Additionally, the coolant flashes off to steam in the case of water, which has a high molecular weight, providing additional fluid dynamic energy to the turbine blades, which increases the mechanical output of the turbine 22.
In an alternate embodiment, rather than the coolant pump 36, the electrical power generation system 20 may be configured to condense water generated in the combustor 30 (steam is a product produced from the fuel-oxidizer reaction itself) through a heat exchanger. The water may then be pumped and injected into the combustor 30 again to cool down the combustion temperature. Such an embodiment advantageously eliminates the added weight of carrying a water reservoir onboard the vehicle 14.
As noted above, the resultant combustion mixture is routed to the turbine to covert the chemical energy of the combustion mixture to mechanical energy in the form of rotation of the turbine blades and the turbine rotor 28. The liquid oxidant stored onboard the vehicle 14 alleviates the issue of not having readily available air, including atmospheric oxygen gas, that is typically ingested into a compressor and subsequently mixed with fuel in a combustor. Illustrative examples of liquid oxidants that may be employed include nitrous oxide, hydrogen peroxide, and liquid oxygen, however, it is to be understood that suitable alternative are contemplated. Therefore, the turbine engine 22 is a bi-propellant turbo system that relies solely on a liquid fuel and a liquid oxidant, both of which are stored onboard the vehicle 14.
Referring now to
In some embodiments, it is desirable to manipulate the rotational output speed of the turbine rotor 28 in order to reduce the output speed to a speed that is suitable for the generator 40. In such embodiments, a gear reduction arrangement 50 is provided, as shown in
Advantageously, the ability to combine a liquid fuel with a liquid oxidant gives the bi-propellant turbo-generator the ability to operate at extremely high altitudes or undersea, where atmospheric oxygen is not readily available.
While the disclosure has been described in detail in connection with only a limited number of embodiments, it should be readily understood that the disclosure is not limited to such disclosed embodiments. Rather, the disclosure can be modified to incorporate any number of variations, alterations, substitutions or equivalent arrangements not heretofore described, but which are commensurate with the scope of the disclosure. Additionally, while various embodiments of the disclosure have been described, it is to be understood that aspects of the disclosure may include only some of the described embodiments. Accordingly, the disclosure is not to be seen as limited by the foregoing description, but is only limited by the scope of the appended claims.
