Patent Application
20200354070
The subject matter disclosed herein generally relates to electrical systems, and more specifically to generating electrical power for electrical systems.
Hypersonic vehicles commonly employ rocket and scramjet engines for propulsion. Rocket engines operate by flowing a flow of high pressure gases through a nozzle, which converts the internal energy on high pressure gases into a propulsive force according to the geometry of the nozzle. Scramj et engines operate combusting fuel in a supersonic airflow, supersonic airflow provided by the forward velocity of the vehicle, which allow the engine to decelerates the air such that pressure and temperature increase. Fuel is introduced into the pressurized and heated air, the mixture ignited, and the resulting high pressure combustion product communicated to a nozzle. The nozzle generates thrust using the high pressure combustion products.
Rockets and scramjet engines generally do not employ rotating components suitable to supply mechanical rotation to generators and hydraulic pumps. It is therefore necessary for a hypersonic vehicles to carry an auxiliary power unit (APU) device to generate power for electrical and hydraulic devices carried by the vehicle. Examples of such APU devices include combustion gas powered APU devices, cold gas powered APU devices, and APU devices with dedicated fuel supplies. Hot gas APU devices typically generate power using hot gases extracted from the engine. Cold gas powered APU devices generally route compressed fuel or propellant, such as helium or hydrogen gas carried by the vehicle, through a cold-gas turbine to generate electric power. Dedicated fuel APU devices typically carry a supply of fuel dedicated for the APU device, typically with a fuel system separate and apart from that which supplies the engine. Each of these approaches require that the vehicle carry fuel sufficient for operation of the APU device during flight of the vehicle.
Such systems and methods have generally been satisfactory for their intended purpose. However, a need remains for improved power modules, vehicles, and power generation methods. The present disclosure provides a solution to this need.
In an embodiment a power module is provided. The power module includes a turbo-generator with a propellant selector valve, a stored energy module connected to the propellant selector valve, and a bleed air conduit. The bleed air conduit is connected to the propellant selector valve and has a diverter element with a first position and a second position. The stored energy module in fluid communication with the turbo-generator while the diverter is in the first position and the bleed air conduit in fluid communication with the turbo-generator while the diverter is in the second position.
In addition to one or more of the features described above, or as an alternative, further embodiments may include a scramjet engine connected to the propellant selector valve by the bleed air conduit.
In addition to one or more of the features described above, or as an alternative, further embodiments may include that the scramjet engine has an inlet segment with a bleed port in fluid communication with a nozzle segment through a combustor segment and an isolator segment, wherein the bleed port is in fluid communication with the bleed air conduit.
In addition to one or more of the features described above, or as an alternative, further embodiments may include that the scramjet engine has a high temperature and high pressure zone, the scramjet engine having a bleed port fluidly coupling the high temperature and high pressure zone with the bleed air conduit.
In addition to one or more of the features described above, or as an alternative, further embodiments may include a gas generator connecting the propellant selector valve to the turbo-alternator.
In addition to one or more of the features described above, or as an alternative, further embodiments may include that the gas generator comprises a decomposition chamber for decomposing a mono-propellant.
In addition to one or more of the features described above, or as an alternative, further embodiments may include that the gas generator comprises a combustion chamber for combusting a bi-propellant with an oxidizer.
In addition to one or more of the features described above, or as an alternative, further embodiments may include that the stored energy module comprises a pressure vessel, wherein the pressure vessel is connected to the propellant selector valve.
In addition to one or more of the features described above, or as an alternative, further embodiments may include that the stored energy module further comprises a compressed gas contained within the pressure vessel.
In addition to one or more of the features described above, or as an alternative, further embodiments may include that the stored energy module includes a mono-propellant contained within the pressure vessel, and a pressurization gas contained within the pressure vessel, the pressurization gas pressurizing the mono-propellant to urge the mono-propellant toward the propellant selector valve.
In addition to one or more of the features described above, or as an alternative, further embodiments may include that the pressure vessel is a bi-propellant pressure vessel, the stored energy module including a bi-propellant contained within the bi-propellant pressure vessel, a pressurization gas pressure vessel connected to the bi-propellant pressure vessel and therethrough in fluid communication with the propellant selector valve, and a pressurization gas contained in the pressurization gas pressure vessel and the bi-propellant pressure, the pressurization gas urging the bi-propellant toward the propellant selector valve.
In addition to one or more of the features described above, or as an alternative, further embodiments may include that the pressure vessel is a bi-propellant pressure vessel, the stored energy module further including an oxidizer pressure vessel connected to the propellant selector valve, a pressurization gas pressure vessel connected to the oxidizer pressure vessel and the bi-propellant pressure vessel, the pressurization gas pressure vessel in fluid communication with the turbine speed control valve through both the pressurization gas pressure vessel and the oxidizer pressure vessel.
In addition to one or more of the features described above, or as an alternative, further embodiments may include that the propellant selector valve is configured to move between the first position and the second position according to energy within an inlet segment of a scramjet engine.
In addition to one or more of the features described above, or as an alternative, further embodiments may include that the propellant selector valve is configured to move from the first position to the second position when energy within an inlet segment of the scramjet engine exceeds a predetermined value.
In addition to one or more of the features described above, or as an alternative, further embodiments may include the turbo-generator includes a turbine connected to the propellant selector valve, an interconnect shaft connected to the turbine, and a permanent magnet generator operably connected to the turbine by the interconnect shaft.
In another embodiment a vehicle is provided. The vehicle includes an airframe carrying a scramjet engine and a power module as described above, the scramjet engine connected to the propellant selector valve by the bleed air conduit, the stored energy module including a pressure vessel that is connected to the propellant selector valve, and the propellant selector valve configured to move from the first position to the second position when energy within an inlet segment of the scramjet engine exceeds a predetermined value.
In addition to one or more of the features described above, or as an alternative, further embodiments the vehicle may include a compressed gas, a mono-propellant and a pressurization gas, or a bi-propellant and a pressurization gas contained within the pressure vessel.
In a further embodiment a method of generating electrical power is provided. The method includes, at a turbo-generator with a propellant selector valve, a stored energy module connected to the propellant selector valve, and a bleed air conduit connected to the propellant selector valve having a diverter element with a first position and a second position, placing the stored energy module in fluid communication with the turbo-alternator by moving the diverter element to the first position, generating electrical power with the turbo-alternator using energy provided by the stored energy module, placing the bleed air conduit in fluid communication with the turbo-alternator by moving the diverter element to the second position, and generating electrical power the turbo-alternator using energy provided by an inlet segment of a scramjet engine through the bleed air conduit.
In addition to one or more of the features described above, or as an alternative, further embodiments may include determining an energy level within the inlet segment of the scramjet engine, moving the diverter element to the first position when the energy level is below a predetermined level, and moving the diverter element to the second position when the energy level is above the predetermined level.
In addition to one or more of the features described above, or as an alternative, further embodiments may include the diverter element is moved between the first position and the second position based on speed of a vehicle carrying the power module.
Technical effects of embodiments of the present disclosure include the capability to generate hydraulic and/or electrical power on a vehicle that does not have a source of rotational power for a generator. In certain embodiments the amount of mono-propellant or fuel utilized for power generation on the vehicle is reduced by employing bleed air from the vehicle propulsion system.
The foregoing features and elements may be combined in various combinations without exclusivity, unless expressly indicated otherwise. These features and elements as well as the operation thereof will become more apparent in light of the following description and the accompanying drawings. It should be understood, however, that the following description and drawings are intended to be illustrative and explanatory in nature and non-limiting.
The following descriptions should not be considered limiting in any way. With reference to the accompanying drawings, like elements are numbered alike:
Reference will now be made to the drawings wherein like reference numerals identify similar structural features or aspects of the subject disclosure. For purposes of explanation and illustration, and not limitation, an exemplary embodiment of a power module in accordance with the disclosure is shown in
Referring to
The power module 100 includes a turbo-generator 104 with a propellant selector valve 106. The turbo-generator 104 is connected through the propellant selector valve 106 to both the stored energy module 108 and the scramjet engine 14, the scramjet being connecting to the propellant selector valve 106 through the bleed air conduit 110. The propellant selector valve 106 is arranged to place the turbo-generator 104 in fluid communication with either the stored energy module 108 or the scramjet engine 14 to generate the electrical power P according to the selected source of energy for turbo-generator 104. In the illustrated implementation the propellant selector valve 106 has a diverter element 112 (shown in
While the diverter element 112 is in the first position A the propellant selector valve 106 connects the stored energy module 108 to the turbo-generator 104 to provide energy 30 to the turbo-alternator from the stored energy module 108. While the diverter element 112 is in the second position B the propellant selector valve 106 connects the scramjet engine 14 (shown in
With reference to
The power converter 118 is electrically connected to the turbo-generator 104 to receive electrical power from the turbo-generator 104. The power converter 118 is also connected to the electrical load 16 (shown in
The turbo-generator 104 includes a permanent magnet generator 120 and a turbine 122. The permanent magnet generator 120 is operatively associated with the turbine 122 and includes one or more permanent magnet 124 and one or more coil or stator winding 126. The one or more permanent magnet 124 is electromagnetically coupled to the one or more coil or stator winding 126. In this respect the permanent magnet generator 120 is configured to convert mechanical rotation R communicated to the permanent magnet generator 120 by the turbine 122 into the electrical power p by rotating the one or more permanent magnet 124 relative to the one or more coil or stator winding 126. In certain embodiments the turbo-generator 104 includes an interconnect shaft 128, which connects the turbine 122 to the permanent magnet generator 120 to communicate mechanical rotation R from the turbine 122 into the electrical power p. It is contemplated that the interconnect shaft 128 directly connect the turbine 122 to the permanent magnet generator 120, e.g., without an intervening gear train, simplifying the arrangement of the power module 100 by eliminating the need for an intervening gear assembly, such as an accessory gearbox.
The turbine 122 is operably connected to the permanent magnet generator 120 and is further connected to the propellant selector valve 106 by the turbine feed conduit 116. In this respect the turbine 122 is in fluid communication with the propellant selector valve 106 through the turbine feed conduit 116 and is configured to receive therefrom the energy 28 (shown in
The stored energy module 108 includes one or more pressure vessel 134. The one or more pressure vessel 134 contains the compressed gas 132 and is connected to the propellant selector valve 106, and therethrough to the turbine 122. In this respect the stored energy module 108 is in fluid communication with the propellant selector valve 106 and is arranged to provide thereto a flow of the compressed gas 132 selectively, e.g., according to temperature and pressure conditions within the scramjet engine 14. In certain embodiments the compressed gas 132 can be compressed helium or compressed hydrogen, by way of non-limiting examples. Utilization of helium and/or hydrogen in the stored energy module 108 simplifies integration of the power module 100 into the vehicle 10 (shown in
The propellant selector valve 106 includes the diverter element 112 and connects both the stored energy module conduit 114 and the bleed air conduit 110 to the turbine feed conduit 116. While in the first position A the diverter element 112, and thereby the propellant selector valve 106, fluidly connects the stored energy module conduit 114 to the turbine feed conduit 116. So connected, the stored energy module 108, and more particularly the one or more pressure vessel 134, provides a flow of the compressed gas 132 to the propellant selector valve 106. The propellant selector valve 106 in turn communicates the flow of the compressed gas 132 to the turbine 122 through the turbine feed conduit 116 via the turbine control valve 105, which is configured for throttling the flow of fluid flowing therethrough to control the turbine 122. As will be appreciated by those of skill in the art in view of the present disclosure, the flow of the compressed gas 132 in turn serves as the source of the mechanical rotation R, which causes the power module 100 to generate electric power P from the energy 30 (shown in
With reference to
With reference to
The stored energy module 208 includes one or more mono-propellant pressure vessel 246 and one or more pressurization gas pressure vessel 248. The one or more mono-propellant pressure vessel 246 is in fluid communication with the stored energy module conduit 114, and therethrough to the gas generator 240 and the decomposition chamber 242, and contains the mono-propellant 244. The one or more pressurization gas pressure vessel 248 is connected to the one or more mono-propellant pressure vessel 246, is in fluid communication therewith, and is in fluid communication therethrough with the stored energy module conduit 114 and the gas generator 240. The one or more pressurization gas pressure vessel 248 contains a pressurization gas 250, such as an inert gas like carbon dioxide or pure nitrogen by way of non-limiting example. The pressurization gas 250 is partially contained within the one or more mono-propellant pressure vessel 246 to pressurize, and thereby communicate according to the position of the diverter element 112, the mono-propellant 244 contained within the mono-propellant pressure vessel 246.
As shown in
As shown in
With reference to
The stored energy module 308 includes one or more bi-propellant pressure vessel 348, one or more oxidizer pressure vessel 350, and one or more pressurization gas pressure vessel 352. The one or more bi-propellant pressure vessel 348 is in fluid communication with a first stored energy module conduit 354, and therethrough to the gas generator 340 and the combustion chamber 342, and contains the bi-propellant 344. The one or more oxidizer pressure vessel 350 is in fluid communication with a second stored energy module conduit 356, and therethrough to the gas generator 340 and the combustion chamber 342, and contains the oxidizer 346. The one or more pressurization gas pressure vessel 352 is connected to both the one or more bi-propellant pressure vessel 348 and the one or more oxidizer pressure vessel 350, is in fluid communication therewith, and is in fluid communication therethrough with the propellant selector valve 306. The one or more pressurization gas pressure vessel 352 contains a pressurization gas 358, such as an inert gas like carbon dioxide or pure nitrogen by way of non-limiting example, for pressurizing the propellant 344 and the oxidizer 346 contained within the one or more bi-propellant pressure vessel 348 and the one or more oxidizer pressure vessel 350, respectively. It is contemplated that the pressurization gas 358 be partially contained within the one or more bi-propellant pressure vessel 348 and the one or more oxidizer pressure vessel 350 to drive the bi-propellant 344 and oxidizer 346 for provision to the gas generator 340 while the propellant selector valve 306 is in the first position A.
The propellant selector valve 306 has a shuttle diverter element 360. The shuttle diverter element 360 is similar to the diverter element 112, and is additionally arranged to connect both the first stored energy module conduit 354 and the second stored energy module conduit 356 to the gas generator 340 when in the first position A. As shown in
As shown in
It is contemplated that the movement of the shuttle diverter element 360 between the first position A and the second position B be according to the flight regime of the vehicle 10 (shown in
With reference to
In certain embodiments the diverter element 112 can be passively shuttled. For example, the diverter can move between the first position A and the second position B according to differential pressure (if the energy storage pressure is higher than the scramjet pressure, the delta pressure, between the energy storage pressure and the scramjet pressure, forces the valve to the energy storage open position, but as the scramjet pressure rises, it pushes against the energy storage pressure force, once the scramjet pressure exceeds the energy storage pressure, the valve is shuttled by the differential pressure between the two pressures to passively select the scramjet source).
With reference to
As shown with box 540, when the energy level is above the predetermined level the bleed air conduit is placed in fluid communication with the turbo-alternator. The bleed air conduit is placed in fluid communication with the turbo-alternator by moving the diverter element to the second position, e.g., the second position B (shown in
Hypersonic propulsion systems, such as rocket engines and scramjet engines are commonly employed to propel vehicles at hypersonic speeds, typically without the use of rotary elements like gas turbine engine cores and crankshafts on internal combustion engines. While it can simplify the operation of such engines, the absence of a source of mechanical rotation means that electrical power need be provided by a dedicated source of mechanical rotation and a dedicated source of energy. The advantages associated with having a source of electrical power on such aircraft generally justifies the loss of payload space and weight by the energy source carried by such vehicles for power generation.
In embodiments described herein the energy carried by the vehicle for electrical power generation is augmented by the energy available from the movement of the vehicle. In this respect energy from a stored energy module carried by the vehicle is utilized during flight regimes where energy is unavailable from the engine for electrical power generation, such as during initial acceleration to hypersonic speed and during the terminal portion of deceleration from hypersonic speed at the end of a flight. Between these intervals, e.g., during the terminal portion of acceleration to hypersonic flight, flight at hypersonic speeds, and the initial portion of deceleration from hypersonic speed, energy provided by the engine is used to generate electric power. This reduces the amount of compressed gas, mono-propellant, and/or bi-propellant and oxidizer that the vehicle must carry to generate electrical power during flight, available space and weight for vehicle payload and/or flight duration commensurately increasing.
The term “about” is intended to include the degree of error associated with measurement of the particular quantity based upon the equipment available at the time of filing the application. For example, “about” can include a range of ±8% or 5%, or 2% of a given value.
The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the present disclosure. 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” and/or “comprising,” when used in this specification, 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, element components, and/or groups thereof.
While the present disclosure has been described with reference to an exemplary embodiment or embodiments, it will be understood by those skilled in the art that various changes may be made and equivalents may be substituted for elements thereof without departing from the scope of the present disclosure. In addition, many modifications may be made to adapt a particular situation or material to the teachings of the present disclosure without departing from the essential scope thereof. Therefore, it is intended that the present disclosure not be limited to the particular embodiment disclosed as the best mode contemplated for carrying out this present disclosure, but that the present disclosure will include all embodiments falling within the scope of the claims.
