# US 11,299,279 B2 · Chilled working fluid generation and separation for an aircraft

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- Number: US 11,299,279 B2
- Document ID: US11299279B2
- Status: Granted
- Kind: B2
- Application number: 16/361,482
- Filed: 2019-03-22
- Published: 2019-09-26
- Granted: 2022-04-12
- Earliest claimed: 2018-03-23
- Assignees: Raytheon Technologies Corporation
- Applicants: United Technologies Corporation
- Inventors: Michael Winter
- Web page: https://patentgrep.com/patent/US11299279B2

## CPC

- B64D 13/08: the air being heated or cooled
- B01D 45/08: by impingement against baffle separators
- B01D 53/002: {by condensation}
- B03C 1/288: {disposed at the outer circumference of a recipient}
- B64D 13/06: the air being conditioned (pressurising B64D13/02)
- B64D 27/12: within, or attached to, wings
- B64D 33/08: of power plant cooling systems
- F01D 15/00: Adaptations of machines or engines for special use; Combinations of engines with devices driven thereby
- F01D 25/12: Cooling
- F02C 6/08: the gas being bled from the gas-turbine compressor
- F02C 7/141: of working fluid
- F02C 7/143: before or between the compressor stages
- F02C 7/16: characterised by cooling medium
- F02C 7/185: {Cooling means for reducing the temperature of the cooling air or gas}
- F02C 9/18: by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages {(F02C3/113 takes precedence)}
- F02K 3/06: with front fan
- F17C 7/02: Discharging liquefied gases
- F17C 7/04: with change of state, e.g. vaporisation
- F25B 9/14: characterised by the cycle used, e.g. Stirling cycle
- F25J 1/0012: {Primary atmospheric gases, e.g. air}
- F25J 1/0035: {by gas expansion with extraction of work}
- F25J 1/0221: {using the cold stored in an external cryogenic component in an open refrigeration loop}
- F25J 1/0275: {adapted for special use of the liquefaction unit, e.g. portable or transportable devices}
- F25J 3/04254: {using the cold stored in external cryogenic fluids (closed loop F25J3/04278)}
- F25J 3/0429: {of feed air, e.g. used as waste or product air or expanded into an auxiliary column}
- F25J 3/04533: {for the direct combustion of fuels in a power plant, so-called "oxyfuel combustion"}
- F25J 3/04563: {Integration with a nitrogen consuming unit, e.g. for purging, inerting, cooling or heating}
- F25J 3/046: {Completely integrated air feed compression, i.e. common MAC}
- F25J 3/04636: {using a hybrid air separation unit, e.g. combined process by cryogenic separation and non-cryogenic separation techniques (F25J3/04733 and F25J3/04757 take precedence)}
- F25J 3/04975: {adapted for special use of the air fractionation unit, e.g. transportable devices by truck or small scale use}
- B64D 37/32: Safety measures not otherwise provided for, e.g. preventing explosive conditions
- B64D 2013/0614: {with subsystems for cooling avionics}
- B64D 2013/0659: {comprising provisions for cooling fuel systems}
- B64D 2013/0674: {comprising liquid subsystems}
- B64D 2013/0677: {comprising on board oxygen generator systems}
- B64D 2013/0681: {with oxygen control}
- F05D 2220/323: for aircraft propulsion, e.g. jet engines
- F05D 2260/205: Cooling fluid recirculation, i.e. after cooling one or more components is the cooling fluid recovered and used elsewhere for other purposes
- F05D 2260/211: by intercooling, e.g. during a compression cycle
- F05D 2260/232: characterized by the cooling medium
- F05D 2260/60: Fluid transfer
- F25J 2205/86: using electrical phenomena, e.g. Corona discharge, electrolysis or magnetic field
- F25J 2210/40: Air or oxygen enriched air, i.e. generally less than 30mol% of O2
- F25J 2215/40: Air or oxygen enriched air, i.e. generally less than 30mol% of O2
- F25J 2230/08: Cold compressor, i.e. suction of the gas at cryogenic temperature and generally without afterstage-cooler
- F25J 2230/30: Compression of the feed stream
- F25J 2240/42: the fluid being air
- F25J 2240/80: Hot exhaust gas turbine combustion engine
- F25J 2290/70: Processing device is mobile or transportable, e.g. by hand, car, ship, rocket engine etc.
- Y02T 50/50: On board measures aiming to increase energy efficiency
- Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft
- B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B01D: SEPARATION (separating solids from solids by wet methods B03B, B03D; by pneumatic jigs or tables B03B; by other dry methods B07; magnetic or electrostatic separation of solid materials from solid materials or fluids, separation by high-voltage electric fields B03C; centrifuges, vortex apparatus B04; presses per se for squeezing-out liquid from liquid-containing material B30B9/02; treatment of water C02F, e.g. softening by ion-exchange C02F1/42; {arrangements of air intake cleaners in gas turbine plants F02C7/05} ; arrangements or mounting of filters in air-conditioning, air-humidification or ventilation F24F13/28)
- B03C: MAGNETIC OR ELECTROSTATIC SEPARATION OF SOLID MATERIALS FROM SOLID MATERIALS OR FLUIDS; SEPARATION BY HIGH-VOLTAGE ELECTRIC FIELDS (separating isotopes B01D59/00; combinations of magnetic or electrostatic separation with separation of solids by other means B03B, B07B)
- F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D)
- F02C: GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS (construction of turbines F01D; jet-propulsion plants F02K; construction of compressors or fans F04; generating combustion products of high pressure or high velocity F23R; using gas turbines in compression refrigeration plants F25B11/00)
- F02K: JET-PROPULSION PLANTS (features of jet-propulsion plants common to gas-turbine plants, air intakes or fuel supply control of air-breathing jet-propulsion plants F02C7/00, F02C9/00)
- F17C: VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES (storing fluids in natural or artificial cavities or chambers in the earth B65G5/00; construction or assembling of bulk storage containers employing civil-engineering techniques E04H7/00; variable-capacity gas-holders F17B; liquefaction or refrigeration machines, plants, or systems F25)
- F25B: REFRIGERATION MACHINES, PLANTS OR SYSTEMS; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS
- F25J: LIQUEFACTION, SOLIDIFICATION OR SEPARATION OF GASES OR GASEOUS {OR LIQUEFIED GASEOUS} MIXTURES BY PRESSURE AND COLD TREATMENT {OR BY BRINGING THEM INTO THE SUPERCRITICAL STATE (cryogenic pumps F04B37/08; gas storage vessels, gas holders F17; filing vessels with, or discharging from vessels, compressed, liquefied or solidified gases F17C; refrigeration machines, plants, or systems F25B)}
- F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION

## Abstract

A system for an aircraft includes an engine bleed source of a gas turbine engine. The system also includes a means for chilling an engine bleed air flow from the engine bleed source to produce a chilled working fluid. The system further includes a means for providing the chilled working fluid for an aircraft use.

## Claims

### Claim 1

A system for an aircraft, the system comprising:
an engine bleed source of a gas turbine engine;
a means for chilling an engine bleed air flow from the engine bleed source to produce a chilled working fluid at a temperature below a boiling point of oxygen and above a boiling point of nitrogen;
a means for separating gaseous nitrogen from the chilled working fluid as a gaseous nitrogen supply and separating liquid oxygen from the chilled working fluid as a liquid oxygen supply; and
a plumbing system comprising:
a feeder line coupled to an output of the means for chilling the engine bleed air flow;
a pump in fluid communication with the feeder line, the pump operable to urge the chilled working fluid for an aircraft use through the plumbing system; and
a valve operable to direct a portion of the chilled working fluid to the means for separating gaseous nitrogen.

### Claim 2 (depends on 1)

The system of claim 1, wherein the means for chilling the engine bleed air flow is a cryogenic cooling system comprising a compressor operable to further compress the engine bleed air flow as compressed air and at least one turbine operable to expand and cool the compressed air as the chilled working fluid.

### Claim 3 (depends on 1)

The system of claim 1, wherein the aircraft use comprises cooling one or more components of the aircraft.

### Claim 4 (depends on 1)

The system of claim 1, wherein the aircraft use comprises an increased airflow to one or more of: components of the gas turbine engine, a cabin of the aircraft, and electronics of the aircraft.

### Claim 5 (depends on 1)

The system of claim 1, wherein the means for separating gaseous nitrogen and liquid oxygen is an impact plate-based separator comprising an impact plate positioned proximate to an input port to alter a flow direction of the chilled working fluid.

### Claim 6 (depends on 1)

The system of claim 1, wherein the means for separating gaseous nitrogen and liquid oxygen is a stagnation plate-based separator comprising a stagnation plate with variations in curvature and flow paths to alter a flow velocity and pressure of the chilled working fluid.

### Claim 7 (depends on 1)

The system of claim 1, wherein the means for separating gaseous nitrogen and liquid oxygen is a magnetic-based separator comprising a magnetic field generator operable to produce a magnetic field to attract the liquid oxygen towards a liquid oxygen output port.

### Claim 8 (depends on 1)

The system of claim 1, wherein at least a portion of the gaseous nitrogen supply is provided to one or more of: a fuel system of the aircraft and a location downstream of a combustor of the gas turbine engine.

### Claim 9 (depends on 1)

The system of claim 1, wherein at least a portion of the liquid oxygen supply is provided to one or more of: a cabin of the aircraft and a compressor stream of the gas turbine engine.

### Claim 10

A method comprising:
providing an engine bleed air flow from an engine bleed source of a gas turbine engine to a cryogenic cooling system;
chilling the engine bleed air flow using the cryogenic cooling system to produce a chilled working fluid at a temperature below a boiling point of oxygen and above a boiling point of nitrogen;
urging, by a pump in fluid communication with a feeder line of a plumbing system, the chilled working fluid from the feeder line for an aircraft use of an aircraft through the plumbing system, wherein the feeder line is coupled to an output of the cryogenic cooling system;
directing, by a valve of the plumbing system, a portion of the chilled working fluid to a cryogenic air separator;
separating, by the cryogenic air separator, gaseous nitrogen from the chilled working fluid as a gaseous nitrogen supply; and
separating, by the cryogenic air separator, liquid oxygen from the chilled working fluid as a liquid oxygen supply.

### Claim 11 (depends on 10)

The method of claim 10, further comprising:
compressing the engine bleed air flow as compressed air by a compressor of the cryogenic cooling system; and
expanding and cooling the compressed air as the chilled working fluid by at least one turbine of the cryogenic cooling system.

### Claim 12 (depends on 10)

The method of claim 10, wherein the aircraft use comprises cooling one or more components of the aircraft.

### Claim 13 (depends on 10)

The method of claim 10, wherein the aircraft use comprises an increased airflow to one or more of: components of the gas turbine engine, a cabin of the aircraft, and electronics of the aircraft.

### Claim 14 (depends on 10)

The method of claim 10, wherein separating gaseous nitrogen and liquid oxygen is performed using an impact plate-based separator comprising an impact plate positioned proximate to an input port to alter a flow direction of the chilled working fluid.

### Claim 15 (depends on 10)

The method of claim 10, further comprising:
providing at least a portion of the gaseous nitrogen supply to one or more of: a fuel system of the aircraft and a location downstream of a combustor of the gas turbine engine.

### Claim 16 (depends on 10)

The method of claim 10, further comprising:
providing at least a portion of the liquid oxygen supply to one or more of: a cabin of the aircraft and a compressor stream of the gas turbine engine.