WO2020210179A1 - Systèmes de production d'air non vicié et leurs procédés d'utilisation - Google Patents

Systèmes de production d'air non vicié et leurs procédés d'utilisation Download PDF

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Publication number
WO2020210179A1
WO2020210179A1 PCT/US2020/026982 US2020026982W WO2020210179A1 WO 2020210179 A1 WO2020210179 A1 WO 2020210179A1 US 2020026982 W US2020026982 W US 2020026982W WO 2020210179 A1 WO2020210179 A1 WO 2020210179A1
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Prior art keywords
chamber
nitrous oxide
vitiated air
vitiated
generating non
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PCT/US2020/026982
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English (en)
Inventor
Joseph Roger HERDY
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Teledyne Brown Engineering, Inc.
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Publication of WO2020210179A1 publication Critical patent/WO2020210179A1/fr

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    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
    • G01M9/02—Wind tunnels
    • G01M9/04—Details
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/83—Testing, e.g. methods, components or tools therefor
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
    • G01N3/30—Investigating strength properties of solid materials by application of mechanical stress by applying a single impulsive force, e.g. by falling weight
    • G01N3/313—Investigating strength properties of solid materials by application of mechanical stress by applying a single impulsive force, e.g. by falling weight generated by explosives

Definitions

  • the present disclosure relates to systems for generating non-vitiated air and methods of use thereof.
  • a system for generating non-vitiated air comprises a nitrous oxide source and a chamber configured to convert the nitrous oxide from the nitrous oxide source into non-vitiated air at a temperature of at least 1,000 degrees Fahrenheit.
  • the chamber comprises a chamber volume (V c ), an inlet, a conversion
  • a method for generating non-vitiated air for hypersonic testing comprises introducing liquid nitrous oxide into a chamber configured to convert the liquid nitrous oxide into non-vitiated air.
  • the chamber comprises a chamber volume (V c ), an inlet, a conversion accelerator, and an outlet.
  • the conversion accelerator is disposed within the chamber and is configured to accelerate conversion of the liquid nitrous oxide into the non-vitiated air.
  • the outlet is configured to receive the non-vitiated air and comprises a throat area (At).
  • a characteristic length, L*, as defined by V c /At of the chamber is at least 1 cm.
  • the liquid nitrous oxide is vaporized into the chamber via the inlet to form a gaseous composition.
  • the gaseous composition is introduced into the conversion accelerator.
  • Non-vitiated air is generated at a temperature of at least 1,000 degrees Fahrenheit.
  • FIG. l is a schematic diagram of an example of a system for generation of non- vitiated air for testing a HS/H device according to the present disclosure
  • FIG. 2 is a schematic diagram of an example of a test system to HS/H devices comprising the system for generation of non-vitiated air according to the present disclosure
  • FIG. 3 is a schematic diagram of an example of a system for generation of non- vitiated air for testing a HS/H device according to the present disclosure.
  • any references herein to“various example,”“some examples,”“one example,”“an example,” or like phrases mean that a particular feature, structure, or characteristic described in connection with the example is included in one example or two or more examples.
  • appearances of the phrases“in various examples,”“in some examples,”“in one examples,” “in an examples,” or like phrases in the specification do not necessarily refer to the same examples.
  • the particular described features, structures, or characteristics may be combined in any suitable manner in one example or two or more examples.
  • the particular features, structures, or characteristics illustrated or described in connection with one example may be combined, in whole or in part, with the features, structures, or characteristics of other examples without limitation. Such modifications and variations are intended to be included within the scope of the present examples.
  • any numerical range recited herein includes all sub-ranges subsumed within the recited range.
  • a range of“1 to 10” includes all sub-ranges between (and including) the recited minimum value of 1 and the recited maximum value of 10, that is, having a minimum value equal to or greater than 1 and a maximum value equal to or less than 10.
  • Any maximum numerical limitation recited in this specification is intended to include all lower numerical limitations subsumed therein and any minimum numerical limitation recited in this specification is intended to include all higher numerical limitations subsumed therein. Accordingly, Applicant reserves the right to amend this specification, including the claims, to expressly recite any sub-range subsumed within the ranges expressly recited. All such ranges are inherently described in this specification.
  • the grammatical articles“a,”“an,” and“the,” as used herein, are intended to include “at least one” or“one or more,” unless otherwise indicated, even if“at least one” or“one or more” is expressly used in certain instances.
  • the foregoing grammatical articles are used herein to refer to one or more than one (i.e., to“at least one”) of the particular identified elements.
  • the use of a singular noun includes the plural and the use of a plural noun includes the singular, unless the context of the usage requires otherwise.
  • High speed / hypersonic (HS/H) devices can travel faster than Mach 5 in flight.
  • HS/H test systems may be used to test the HS/H devices for flight performance however, the current HS/H test systems may produce improper test conditions which are not commensurate with actual flight conditions experienced by the HS/H device.
  • gas can be accelerated to supersonic (i.e., greater than Mach 1) and/or hypersonic (i.e., greater than Mach 5) speed by creating a high pressure ratio in a chamber which introduces isentropic expansion.
  • the gas can be cooled to a temperature that is not commensurate with actual flight of the HS/H device at supersonic and/or hypersonic speed (e.g., one thousand or two thousand degrees Fahrenheit due to drag friction and/or compression effects).
  • the air can be cooled to a temperature due to the isentropic expansion which can condense oxygen out of the air while leaving the nitrogen in a gas phase which causes improper test conditions (e.g., reduced oxygen content).
  • Some HS/H test systems have counteracted the cooling due to isentropic expansion with a ceramic heater or heater comprising a non-oxidizing material which can only generate intense heat for a few seconds, an arc jet heater which results in an improper ionizing environment, and/or an upstream combustion device which can reduce oxygen content and introduce contaminates (e.g., vitiated air) into the test environment.
  • a system for generating non-vitiated air and a method of use thereof are provided which can provide proper test conditions.
  • the present disclosure can produce heated gases simulating the atmospheric constituents of nitrogen and oxygen for creating a hot test environment that can be substantially identical to a HS/H device with an air breathing propulsion systems at supersonic speed and/or hypersonic speed.
  • the present disclosure can enable testing of full duration missions in a realistic test environment.
  • non-vitiated air refers to a gas composition that is substantially free of contaminates (e.g., carbon-based particulate) and comprises a composition substantially similar to atmospheric air.
  • contaminates e.g., carbon-based particulate
  • vitiation contamination can have a profound effect on vibrational relaxation, combustion kinetics, condensation and overall test engine performance.
  • Contaminants include the vitiated species generated by a combustion heater process, namely H2O and CO2 (water and carbon dioxide) (Reference“Experimental and Numerical Studies of Vitiated Air Effects on Hydrogen-fueled Supersonic Combustor Performance”, Chinese Journal of Aeronautics , March 2012).
  • contaminates such as, for example, at least 99% free, at least 99.9% free, at least 99.99% free of contaminates, or 100% free of contaminates, all on a volume basis.
  • the non-vitiated air composition can comprise 10 percent to 45 percent oxygen gas, 55 percent to 90 percent nitrogen gas, and 0 percent to 5 percent of other components, such as, for example, argon, carbon dioxide, neon, helium, and water vapor, all on a volume basis.
  • the non-vitiated air composition can comprise 10 percent to 45 percent oxygen gas, 55 percent to 90 percent nitrogen gas, and 0 percent to 5 percent of other components, such as, for example, argon, carbon dioxide, neon, helium, and water vapor, all on a volume basis.
  • the non-vitiated air composition can comprise 10 percent to 45 percent oxygen gas, 55 percent to 90 percent nitrogen gas, and 0 percent to 5 percent of other components, such as, for example, argon, carbon dioxide, neon, helium, and water vapor, all on a volume basis.
  • a non-vitiated air composition can comprise 15 percent to 35 percent oxygen gas, 65 percent to 85 percent nitrogen gas, and 0 percent to 5 percent of other components, all on a volume basis.
  • a non-vitiated air composition can comprise 18 percent to 24 percent oxygen gas and 76 percent to 82 percent nitrogen gas, all on a volume basis.
  • the non-vitiated air can comprise 21 percent oxygen gas, 78 percent nitrogen gas, and 1 percent of other components, all on a volume basis.
  • the non-vitiated air composition can comprise diatomic and homonuclear oxygen gas and nitrogen gas.
  • Non-vitiated air may not be vitiated air as defined in“CHAPTER 4: AIR VITIATION EFFECTS ON SCRAMJET COMBUSTION TESTS” by G. Pellett, C. Bruno, and W. Chinitz, which is hereby incorporated by reference.
  • a system 100 for generating non-vitiated air for testing a HS/H device comprises a nitrous oxide source 102 and a chamber 104 in fluid communication (e.g., fluid dynamics coupling) with the nitrous oxide source 102.
  • the nitrous oxide source 102 can comprise nitrous oxide 114a and can be configured to introduce the nitrous oxide 114a as a liquid and/or a gaseous composition into the chamber 104.
  • the nitrous oxide 114a can be in a liquid state, a gaseous state, or combinations thereof.
  • the nitrous oxide can be at least 90 percent pure by volume, such as, for example, at least 95 percent pure by volume, at least 99 percent pure by volume, at least 99.9 percent pure by volume, or at least 99.99 percent pure by volume.
  • the nitrous oxide source 102 can comprise a component other than nitrous oxide.
  • the nitrous oxide source 102 can be a nitrogen oxide source.
  • the nitrogen oxide source can comprise NO, Nitrous oxide (N2O), NO2, N2O4, N4O, N2O3, N2O5, N4O6, or combinations thereof.
  • the nitrogen oxide can be a blend with an additional component such as for example hydrogen (e.g., to reduce the oxygen content in the non-vitiated air and/or generate water vapor).
  • the composition of the nitrogen oxide and/or blend can be configured such that non-vitiated air is generated by the system 100 with a desired composition and at desired test conditions.
  • the nitrous oxide can be at room temperature (e.g., 20 degrees Celsius), cooled to a temperature lower than room temperature, or heated to a temperature higher than room temperature.
  • the nitrous oxide can be introduced into the chamber 104 at an inlet pressure of 100 pounds per square inch gauge (psig) or greater, such as, for example, 200 psig or greater, 300 psig or greater, 400 psig or greater, 500 psig or greater, 600 psig or greater, 700 psig or greater, 750 psig or greater, 800 psig or greater, 900 psig or greater, 1,000 psig or greater, 2,000 psig or greater, 3,000 psig or greater, 4,000 psig or greater, or 5,000 psig or greater.
  • psig pounds per square inch gauge
  • the nitrous oxide can be introduced into the chamber 104 at an inlet pressure of 100,000 psig or less, such as, for example, 50,000 psig or less, 40,000 psig or less, 30,000 psig or less, 20,000 psig or less, 10,000 psig or less, 9,000 psig or less, 8,000 psig or less, 7,500 psig or less, 7,000 psig or less, 6,000 psig or less, 5,000 psig or less, 4,000 psig or less, 3,000 psig or less, or 2,000 psig or less.
  • 100,000 psig or less such as, for example, 50,000 psig or less, 40,000 psig or less, 30,000 psig or less, 20,000 psig or less, 10,000 psig or less, 9,000 psig or less, 8,000 psig or less, 7,500 psig or less, 7,000 psig or less, 6,000 psig or less, 5,000 psig or less, 4,000 psig or less,
  • the nitrous oxide can be introduced into the chamber 104 at an inlet pressure in a range of 100 psig to 100,000 psig, such as, for example, 500 psig to 3,000 psig or 750 psig to 3,000 psig.
  • the nitrous oxide can deflagrate at approximately 600 °C (1, 112 °F) at a pressure of 309 psi (21 atmospheres).
  • nitrous oxide can require an ignition energy of 6 joules, whereas nitrous oxide at 130 psi and 600 °C (1,112 °F), a 2,500-joule ignition energy input may not be insufficient. Accordingly, the pressure of the nitrous oxide can be adjusted depending on the desired application and the configuration of the system 100.
  • the chamber 104 can be configured to convert the nitrous oxide 114a from the nitrous oxide source 102 into non-vitiated air 114d at the desired test conditions.
  • the conversion of the nitrous oxide 114a into non-vitiated air 114d can comprise a thermal decomposition, a catalytic decomposition, a shock decomposition, a combustion decomposition, or
  • the nitrous oxide from the nitrous oxide source can undergo a decomposition event in the chamber 104, such as, for example, as discussed in: "Modeling of N20 Decomposition Events" by Arif Karabey oglu, Jonny Dyer, Jose Stevens, and Brian Cantwell. 44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, Joint Propulsion Conferences; U.S. Patent 6,779,335 to Herdy; and/or U.S. Patent 9,598,323 to Herdy, which are all hereby incorporated by reference.
  • the chamber 104 can decompose the nitrous oxide 114a into non-vitiated air 114d at desired test conditions.
  • the non-vitiated air 114d generated by the chamber 104 can comprise desired test conditions, such as, for example, a desired test speed, a desired test composition, a desired test pressure, and a desired test temperature.
  • the desired test speed can be Mach 1 or greater, such as, for example, Mach 2 or greater, Mach 3 or greater, Mach 4 or greater, Mach 5 or greater, Mach 6 or greater, Mach 7 or greater, Mach 8 or greater, Mach 9 or greater, or Mach 10 or greater.
  • the desired test speed can be Mach 20 or less, such as, for example, Mach 10 or less, Mach 9 or less, Mach 8 or less, Mach 7 or less, Mach 6 or less, Mach 5 or less, Mach 4 or less, Mach 3 or less, or Mach 2 or less.
  • the desired test speed can be in a range of Mach 1 to Mach 20, such as, for example, Mach 2 to Mach 10, Mach 3 to Mach 7, or Mach 5 to Mach 10.
  • Mach 1 one times the speed of sounds
  • Mach 2 two times the speed of sound
  • the desired test composition can be a non-vitiated air.
  • the desired test pressure can be 0.01 pounds per square inch absolute (psia) or greater, such as, for example, 1 psia or greater, 2 psia or greater, 3 psia or greater, 4 psia or greater, 5 psia or greater, 10 psia or greater, 14 psia or greater, 14.7 psia or greater, 20 psia or greater, or 30 psia or greater.
  • psia pounds per square inch absolute
  • the desired test pressure can be 50 psia or less, such as, for example, 30 psia or less, 20 psia or less, 14.7 psia or less, 14 psia or less, 10 psia or less, 5 psia or less, 4 psia or less, 3 psia or less, 2 psia or less, or 1 psia or less.
  • the desired test pressure can be in a range of 0.01 psia to 50 psia, such as, for example, lpsia to 30 psia or 1 psia to 14.7 psia.
  • the desired test temperature can be 1,000 degrees Fahrenheit or greater, such as, for example, 2,000 degrees Fahrenheit or greater, 2,500 degrees Fahrenheit or greater, 2,600 degrees Fahrenheit or greater, 2,700 degrees Fahrenheit or greater, 2,800 degrees Fahrenheit or greater, 2,900 degrees Fahrenheit or greater, or 6,000 degrees Fahrenheit or greater.
  • the desired test temperature can be 12,000 degrees Fahrenheit or less, 6,000 degrees Fahrenheit or less, 2,900 degrees Fahrenheit or less, 2,800 degrees Fahrenheit or less, 2,700 degrees Fahrenheit or less, 2,600 degrees Fahrenheit or less, 2,500 degrees Fahrenheit or less, or 2,000 degrees Fahrenheit or less.
  • the desired test temperature can be in a range of 1,000 degrees Fahrenheit to 12,000 degrees Fahrenheit, such as, for example, 2,000 degrees Fahrenheit to 12,000 degrees Fahrenheit or 2,500 degrees Fahrenheit to 12,000 degrees Fahrenheit.
  • the chamber 104 can comprise an inlet 108, an outlet 110, and a conversion accelerator 112.
  • the inlet 108 can be in fluid communication with the nitrous oxide source 102 and can be configured to receive nitrous oxide 114a from the nitrous oxide source 102.
  • the inlet 108 can introduce the nitrous oxide 114a into the chamber 104 and control the flow rate and/or pressure of the nitrous oxide 114a being introduced into the chamber 104.
  • the inlet 108 can comprise an inlet nozzle and/or an inlet valve.
  • the inlet valve can be a divergent/convergent nozzle (e.g., fixed, like a Laval nozzle, or variable with changeable area ratios and dimensions).
  • the inlet nozzle which can be configured to disperse the nitrous oxide 114a into the chamber 104 and/or change the phase of the nitrous oxide 114a.
  • the inlet nozzle can change a liquid nitrous oxide 114a received from the nitrous oxide source 102 and/or pump 106 into a gaseous composition 114b of nitrous oxide which can initiate the conversion of the nitrous oxide 114a into non-vitiated air 114d.
  • the inlet nozzle can vaporize liquid nitrous oxide 114a into the chamber 104 to form gaseous composition 114b and the vaporization of the nitrous oxide 114a can initiate a decomposition of the nitrous oxide 114a into non-vitiated air 114d.
  • Decomposition of the nitrous oxide 114a can be an exothermic process as shown in Formula 1 below.
  • N 2 0 N 2 +— 0 2 + heat
  • A“gaseous composition” as used herein is meant to mean a gas, and optionally a mixture of a gas and a liquid, such as, for example, a vapor, a mist, a gas that has a temperature at least the critical temperature of the substance, or a combination thereof.
  • a gaseous composition of nitrous oxide can comprise nitrous oxide vapor, nitrous oxide mist, nitrous oxide gas, or combinations thereof.
  • a“mist” is meant to mean a substance comprising small droplets of liquid that are suspended in a gas. Mist can vaporize or evaporate into vapor. Mist may not condense, as mist is already in the liquid phase. Mist can be generated with a suitable liquid droplet generating device. Depending on the size and density of the small droplets of liquid, mist is generally visible to the naked eye.
  • a“vapor” is meant to mean a substance in the gas phase that has a temperature lower than the critical temperature of the substance such that the vapor can be condensed to a liquid by increasing the pressure without reducing the temperature. Vapor can condense into a liquid phase from the gas phase. In various examples, nitrous oxide vapor is distinct from nitrous oxide mist.
  • the pressure of the nitrous oxide in the inlet 108 may need to be adjusted to an inlet pressure to achieve a process flow rate of the nitrous oxide 114a into the chamber 104 and/or a desired conversion of nitrous oxide 114a into non-vitiated air 114d.
  • the inlet pressure can be adjusted by the chamber 104 pressure, the inlet nozzle, the inlet valve, a pump 106, or combinations thereof.
  • the pump 106 can be provided in fluid communication with the nitrous oxide source 102 and the inlet 108 of the chamber 104.
  • the pump 106 can receive nitrous oxide 114a from the nitrous oxide source 102 and introduce the nitrous oxide 114a to the inlet 108 of the chamber 104 as liquid nitrous oxide and/or a gaseous composition of nitrous oxide.
  • the pump 106 can keep the phase of the nitrous oxide 114a the same as provided by the nitrous oxide source 102 or change the phase of the nitrous oxide 114a provided from the nitrous oxide source 102 (e.g., gas to a liquid).
  • the pump 106 can change (e.g., increase, decrease) a pressure of the nitrous oxide 114a received from the nitrous oxide source 102 and provide the nitrous oxide 114a to the inlet 108 at the desired pressure.
  • the chamber 104 can comprise a single vessel or multiple vessels as desired.
  • the chamber 104, the pump 106, or combinations along the feed path to the inlet 108 may be temperature conditions as needed.
  • the conversion accelerator 112 can be disposed within the chamber 104 and configured to accelerate the conversion of nitrous oxide 114a into process gas 114c and/or non-vitiated air 114d.
  • chamber 104 can comprise at least two conversion accelerators 112, such as, for example, at least three conversion accelerators 112, at least four conversion accelerators 112, or at least five conversion accelerators 112, or more.
  • the conversion accelerators 112 can be configured in a parallel arrangement, in a series arrangement, or combinations thereof. In examples comprising a parallel arrangement of the conversion accelerators 112, the conversion accelerators 112 can receive different portions of the gaseous composition 114b and simultaneous convert their respective portion into process gas 114c and/or non-vitiated air 114d.
  • a first conversion accelerator can receive the gaseous composition 114b and produce process gas 114c which can be introduced to a second conversion accelerator (not shown).
  • the second conversion accelerator can convert the process gas 114c into a second process gas (not shown) and/or non-vitiated air 114d.
  • the output of the second conversion accelerator can be directed through a chain of additional conversion accelerators (not shown) to produce the non-vitiated air 114d.
  • the characteristic length, L*, while generally applicable to this situation yet classically applicable to rocket engines is herein stipulated to be a length and/or a volume necessary to generate sufficient residence time or stay time for nitrous oxide decomposition.
  • the conversion accelerators 112 can comprise a heater (e.g., ohmic heater, arc heater), a catalyst, a shock tube, a combustion chamber, or combinations thereof.
  • the catalyst can comprise platinum, iridium (e.g., Shell 405), rhodium, tungsten, carbide, copper, cobalt, gold, or combinations thereof.
  • the heating of the gaseous composition 114b by the heater can be by convection, conduction, radiation, or combinations thereof.
  • the heating of the nitrous oxide 114a caused by initiation of the conversion and/or by the conversion accelerators 112 may result in a cascading decomposition of the gaseous composition 114b and/or process gas 114c (e.g., a chain reaction, thermal auto-decomposition, adiabatic decomposition) into the non-vitiated air 114d.
  • process gas 114c e.g., a chain reaction, thermal auto-decomposition, adiabatic decomposition
  • the outlet 110 can be configured to receive the non-vitiated air 114d and the non- vitiated air 114d can have the desired test conditions in the outlet 110 of the chamber 104.
  • the outlet 110 can comprise a throat area, At, which can be defined according to
  • the throat area, At can be related to the diameter of the outlet 110.
  • the outlet 110 can be configured in fluid communication with a HS/H test system 200 as illustrated in FIG. 2 and described herein.
  • the outlet can be coupled to the geometry of the test system 200 as illustrated in FIG. 2.
  • the outlet 110 can comprise an outlet nozzle and a valve.
  • the size of the chamber 104 can be configured to achieve a desired conversion rate of the nitrous oxide 114a into oxygen gas and nitrogen gas.
  • the conversion of nitrous oxide into oxygen gas and nitrogen gas may be 80 percent or greater on a mole basis, such as, for example, 90 percent or greater, 95 percent or greater, 99 percent or greater, or 99.9 percent or greater, all on a mole basis.
  • the chamber 104 can configured with a volume, Vc, according to Formula 2 below.
  • V c is the volume of chamber 104
  • q is the mass flow rate of nitrous oxide 114a into the chamber 104
  • V is the average specific volume of the reactants (e.g., nitrous oxide 114a) and products (e.g., oxygen, nitrogen)
  • t s is the stay time of the nitrous oxide in the chamber 104.
  • the chamber 104 can be configured with a characteristic length, L*, according to Formula 3 below.
  • L* is the characteristic length
  • V c is the volume of chamber 104
  • At is the throat area, At of the outlet 110.
  • the characteristic length, L*, referring again to FIG. 1, of the chamber 104 can be 1 centimeter (cm) or greater, such as, for example, 2 cm or greater, 3 cm or greater, 4 cm or greater, 5 cm or greater, 10 cm or greater, 20 cm or greater, 30 cm or greater, 40 cm or greater, 50 cm or greater, 60 cm or greater, 70 cm or greater, 80 cm or greater, 90 cm or greater, 100 cm or greater, 110 cm or greater, 120 cm or greater, 130 cm or greater, 140 cm or greater, 150 cm or greater, 200 cm or greater, 300 cm or greater, 400 cm or greater, or 500 cm or greater.
  • cm centimeter
  • the characteristic length, L*, of the chamber 104 can be 1 meter (m) or less, such as, for example, 500 cm or less, 400 cm or less, 300 cm or less, 200 cm or less, 150 cm or less, 140 cm or less, 130 cm or less, 120 cm or less, 110 cm or less, 100 cm or less, 90 cm or less, 80 cm or less, 70 cm or less, 60 cm or less, 50 cm or less, 40 cm or less, 30 cm or less, 20 cm or less, 10 cm or less, 5 cm or less, 4 cm or less, 3 cm or less, or 2 cm or less.
  • the characteristic length, L*, of the chamber 104 can be in a range of 1 cm to 1 m, such as, for example, 10 cm to 200 cm or 10 cm to 100 cm.
  • the characteristic length, L*, of the chamber 104 can be configured to achieve the desired conversion rate of the nitrous oxide 114a into oxygen gas and nitrogen gas.
  • the chamber 104 can comprise a port 116 configured to introduce a secondary gas into the chamber 104.
  • the chamber 104 can be configured to mix the secondary gas with the process gas 114c to achieve a desired composition of the non-vitiated air 114d.
  • the secondary gas can comprise nitrogen, oxygen, argon, carbon dioxide, neon, helium, water vapor, or combinations thereof.
  • the secondary gas comprises nitrogen which is at least 95 percent pure, such as, for example, at least 99 percent pure, at least 99.9 percent pure, at least 99.99 percent pure, at least 99.999 percent pure, or at least 99.9999 percent pure, all percentages by volume.
  • the secondary gas comprises nitrogen
  • the secondary gas is introduced into the chamber 104 in order to increase the nitrogen content relative to the oxygen content in the non-vitiated air 114d to achieve a desired composition of the non- vitiated air 114d.
  • a complete decomposition of nitrous oxide forms a mixture comprising 1/3 oxygen and 2/3 nitrogen on a volume basis and the mixture can be adjusted with nitrogen to increase the nitrogen content relative to the oxygen content.
  • the secondary gas can be heated or cooled prior to mixing with the process gas 114c in order to achieve the desired test temperature.
  • the port 116 can be configured to introduce a secondary gas into the inlet 108.
  • the port 116 can introduce the secondary gas into the inlet 108 to mix with the nitrous oxide 114a such that a desired composition of the non-vitiated air 114d is achieved.
  • the secondary gas can be heated or cooled prior to mixing with the nitrous oxide 114a in order to achieve a desired temperature.
  • the port 116 can be configured to introduce the secondary gas into the inlet 108 prior to the pump 106 or after the pump 106.
  • the secondary gas can be introduced into the gaseous composition 114b.
  • the system 100 can comprise a controller 118 configured to control various parameters.
  • the controller 118 can be in signal communication with the nitrous oxide source 102, the pump 106, the inlet 108, the chamber 104, the accelerators 112, the port 116, or combinations thereof.
  • the controller 118 can control the flow rate, pressure, and/or temperature of the nitrous oxide as introduced into the chamber 104.
  • the controller 118 can control the temperature of a catalyst and/or a current to an ohmic heater.
  • the controller 118 can control a flow rate of the gaseous composition of nitrous oxide that is introduced to each conversion accelerators configured in a parallel arrangement.
  • the controller 118 comprises a processing unit operatively coupled to memory.
  • FIG. 2 illustrates a schematic diagram of a test system 200 comprising the system 100 for generation of non-vitiated air.
  • the test system 200 can comprise an inlet system 220, a test chamber 222, ejectors 224, and an exhaust muffler 226.
  • the inlet system 220 can be in fluid communication with the system 100 for generation of non-vitiated air, or alternatively air from an external compressed air supply used for shakedown or diagnostic testing of the test system 200.
  • the test chamber 222 can comprise an inlet port 222a and an outlet port 222b.
  • the inlet port 222a can be in fluid communication with the outlet 110 of the system 100 for generation of non-vitiated air and the outlet port 222b can be in fluid communication with ejectors 224 and exhaust 226.
  • the test chamber 222 can be configured to receive a device to be tested and subject the device to non-vitiated air 114d from the system 100 for generation of non-vitiated air at the desired test conditions.
  • the device can be a HS/H device, such as, for example, an aerospace vehicle or component.
  • the device can be a ramjet, a scram jet, a ducted rocket, a thermal protection system material, a HS/H jet, a drone, a weapons system, an engine, an engine component (e.g., a compressor blade, an isolator, a combustor), a heat exchanger, or combinations thereof.
  • the test chamber 222 along with the ports 222a, 222b may be adjusted in order to control the speed of the non-vitiated air 114d contacting the device to be tested.
  • the outlet port 222b may include baffles and nozzles to receive gas from the test chamber 222.
  • the nozzles may serve to cool and reduce the velocity of gas exiting the test chamber 222.
  • High- altitude testing (HAT) facilities are able to simulate high atmosphere conditions by systematically lowering the air pressure around the nozzle exit by use of the exhaust plumb itself, diffusers, and ejectors.
  • a HAT facility can simulate pressure altitudes of up to and somewhat over 100,000 ft while the engine is running at full capacity. These low pressures are obtained by utilizing the momentum from the exhaust plume, as well as any ejectors that are employed, to pull air out of the testing section of the apparatus.
  • the ejectors 224 can remove air from the test system 200 to reduce the velocity of the gas exiting the test chamber 222.
  • the ejectors 224 can be coupled to high pressure tanks that supply air to the ejectors designed specifically for the altitude conditions needed.
  • the exhaust muffler 226 can reduce sound generated by the flow of gas through the test system 200.
  • a system for generating non-vitiated air for testing a high speed/hypersonic (HS/H) device comprising: a nitrous oxide source; and a chamber configured to convert the nitrous oxide from the nitrous oxide source into non-vitiated air at a temperature of at least 1,000 degrees Fahrenheit, the chamber comprising: a chamber volume, V c ; an inlet in fluid communication with the nitrous oxide source; a conversion accelerator disposed within the chamber and configured to accelerate conversion of the nitrous oxide into the non- vitiated air; and an outlet configured to receive the non-vitiated air and comprising a throat area, At; wherein a characteristic length, L*, as defined by Vc/At of the chamber is at least 1 cm.
  • a hypersonic test system comprising: the system for generating non-vitiated air of any one of clauses 1-12; and a test chamber configured to receive the non-vitiated air from the system for generating non-vitiated air and subject the HS/H device to the non-vitiated air.
  • a method for generating non-vitiated gas for high speed/ hypersonic (HS/H) testing comprising: introducing liquid nitrous oxide into a chamber configured to convert the liquid nitrous oxide into non-vitiated air, the chamber comprising: a chamber volume, V c ; an inlet; a conversion accelerator disposed within the chamber and configured to accelerate conversion of the liquid nitrous oxide into the non-vitiated air; and an outlet configured to receive the non-vitiated air and comprising a throat area, At; wherein a characteristic length, L*, as defined by Vc/At of the chamber is at least 1 cm; vaporizing the liquid nitrous oxide into the chamber via the inlet to form a gaseous composition; introducing the gaseous composition into the conversion accelerator; and generating non-vitiated air at a temperature of at least 1,000 degrees Fahrenheit.
  • introducing the gaseous composition into the conversion accelerator comprises introducing a first portion of the gaseous composition to a first conversion accelerator and a second portion of the gaseous composition to a second conversion accelerator, wherein the first portion is different from the second portion.
  • introducing the gaseous composition into the conversion accelerator comprises introducing the gaseous composition to a first conversion accelerator to produce an intermediate composition and introducing the intermediate composition to a second conversion accelerator to produce the non-vitiated air.
  • non-vitiated air composition comprises: 10 percent to 45 percent oxygen gas based on volume of the non-vitiated air; and 55 percent to 90 percent nitrogen gas based on volume of the non-vitiated air.
  • a system for generating non-vitiated air for testing a high speed/hypersonic (HS/H) device comprising: a nitrous oxide source; and a chamber configured to convert the nitrous oxide from the nitrous oxide source into non-vitiated air at a temperature of at least 1,000 degrees Fahrenheit, the chamber comprising: a chamber volume, V c ; an inlet in fluid communication with the nitrous oxide source; an conversion accelerator disposed within the chamber and configured to accelerate conversion of the nitrous oxide into the non- vitiated air; and an outlet configured to receive the non-vitiated air and comprising a throat area, At; wherein a characteristic length, L*, as defined by Vc/At of the chamber is configured to convert at least 80 percent of nitrous oxide into oxygen gas and nitrogen gas on a mole basis.
  • L* characteristic length
  • a hypersonic test system comprising: the system for generating non-vitiated air of claims 27-35; and a test chamber configured to receive the non-vitiated air from the system for generating non-vitiated air and subject the HS/H device to the non-vitiated air.
  • non-vitiated air composition comprises: 10 percent to 45 percent oxygen gas based on volume of the non-vitiated air; and 55 percent to 90 percent nitrogen gas based on volume of the non-vitiated air.

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  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Fluid Mechanics (AREA)
  • General Physics & Mathematics (AREA)
  • Treating Waste Gases (AREA)

Abstract

L'invention concerne un système de production d'air non vicié et son procédé d'utilisation. Le système comprend une source d'oxyde nitreux et une chambre conçue pour convertir l'oxyde nitreux de la source d'oxyde nitreux en air non vicié à une température d'au moins 1 000 degrés Fahrenheit. La chambre comprend un volume de chambre (Vc), une entrée, un accélérateur de conversion et une sortie. L'entrée est en communication fluidique avec la source d'oxyde nitreux. L'accélérateur de conversion est disposé à l'intérieur de la chambre et conçu pour accélérer la conversion de l'oxyde nitreux en air non vicié. La sortie est conçue pour recevoir l'air non vicié et comprend une zone de gorge (At). Une longueur caractéristique, L*, telle que définie par Vc/At de la chambre est d'au moins 1 cm.
PCT/US2020/026982 2019-04-08 2020-04-07 Systèmes de production d'air non vicié et leurs procédés d'utilisation WO2020210179A1 (fr)

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