# US 11,906,166 B2 · Injector device for an engine device, engine device, and air- and/or spacecraft

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- Number: US 11,906,166 B2
- Document ID: US11906166B2
- Status: Granted
- Kind: B2
- Application number: 17/450,897
- Filed: 2021-10-14
- Published: 2022-04-07
- Granted: 2024-02-20
- Earliest claimed: 2019-04-15
- Assignees: Deutsches Zentrum fuer Luft- und Koeln, Raumfahrt e.V.
- Applicants: Deutsches Zentrum fuer Luft-und Raumfahrt e.V.
- Inventors: Wolfgang Armbruster; Justin Hardi; Michael Oschwald; Yannik Miene; Dmitry Suslov
- Web page: https://patentgrep.com/patent/US11906166B2

## CPC

- F23R 3/28: characterised by the fuel supply (burners F23D)
- F02K 9/52: Injectors
- F02K 9/72: using liquid and solid propellants, i.e. hybrid rocket-engine plants
- F23L 7/007: {Supplying oxygen or oxygen-enriched air}
- F05D 2260/963: by Helmholtz resonators
- F05D 2260/964: counteracting thermoacoustic noise
- F23R 2900/00014: Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators
- Y02E 20/34: Indirect CO2mitigation, i.e. by acting on non CO2directly related matters of the process, e.g. pre-heating or heat recovery
- F23R: GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS (fluidised bed combustion apparatus specially adapted for operation at superatmospheric pressures F23C10/16)
- 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)
- F23L: SUPPLYING AIR OR NON-COMBUSTIBLE LIQUIDS OR GASES TO COMBUSTION APPARATUS IN GENERAL ({air-supply arrangements for fluent fuels F23C;} firebridges with means for feeding air or steam F23M3/04; baffles or shields with air supply passages F23M9/04); VALVES OR DAMPERS SPECIALLY ADAPTED FOR CONTROLLING AIR SUPPLY OR DRAUGHT IN COMBUSTION APPARATUS {(dampers and throat restrictors for open fire-places F24; air inlet valves for open fire fronts F24)}; INDUCING DRAUGHT IN COMBUSTION APPARATUS; TOPS FOR CHIMNEYS OR VENTILATING SHAFTS; TERMINALS FOR FLUES
- F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- Y02E: REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION

## Abstract

An injector device for an engine device for introducing a fluidic, in particular a liquid, fuel and a fluid, in particular liquid, oxidizing agent into a combustion chamber of the engine device is provided. The injector device defines a longitudinal axis and comprises at least one first injection element, which is configured in the form of a first fluid channel for fluidically connecting a first collection space for the fluidic oxidizing agent and the combustion chamber, and at least one second injection element, which is configured in the form of a second fluid channel for fluidically connecting a second collection space for the fluidic fuel and the combustion chamber. At least one first resonator element is associated with the at least one first injection element and/or at least one second resonator element is associated with the at least one second injection element.

## Claims

### Claim 1

An injector device for an engine device for introducing a fluidic fuel and a fluidic oxidizing agent into a combustion chamber of the engine device, which injector device defines a longitudinal axis and comprises at least one first injection element, which is configured in the form of a first fluid channel for fluidically connecting a first collection space for the fluidic oxidizing agent and the combustion chamber, and at least one second injection element, which is configured in the form of a second fluid channel for fluidically connecting a second collection space for the fluidic fuel and the combustion chamber,
wherein at least one of at least one first resonator element is associated with the at least one first injection element and at least one second resonator element is associated with the at least one second injection element, and
wherein at least one of the at least one first resonator element is adapted to an eigenfrequency of the associated at least one first injection element and the at least one second resonator element is adapted to an eigenfrequency of the associated at least one second injection element,
wherein at least one of:
the at least one first resonator element and the first collection space are fluidically connected to one another by way of a first flushing channel, so that the fluid flowing through the at least one first injection element also flows at a flow speed through the at least one first resonator element, thereby ensuring that the same conditions prevail in the at least one first resonator element at any one time as in the at least one first injection element to be dampened, and
the at least one second resonator element and the second collection space are fluidically connected to one another by way of a second flushing channel, so that the fluid flowing through the at least one second injection element also flows at a flow speed through the at least one second resonator element, thereby ensuring that the same conditions prevail in the at least one second resonator element at any one time as in the at least one second injection element to be dampened.

### Claim 2 (depends on 1)

The injector device in accordance with claim 1, wherein at least one of:
a) the at least one of the at least one first resonator element is fluidically connected to the at least one first injection element,
the at least one second resonator element is fluidically connected to the at least one second injection element,
and
b) at least one of the at least one first resonator element comprises a first resonator cavity, which defines a first resonator volume, and wherein a first resonator channel fluidically connects the at least one first injection element and the first resonator cavity, and
the at least one second resonator element comprises a second resonator cavity, which defines a second resonator volume, and wherein a second resonator channel fluidically connects the at least one second injection element and the second resonator cavity.

### Claim 3 (depends on 1)

The injector device in accordance with claim 1, wherein at least one of:
a) the at least one first injection element defines a first injection element longitudinal axis, and
b) the at least one second injection element defines a second injection element longitudinal axis.

### Claim 4 (depends on 1)

The injector device in accordance with claim 1, wherein at least one of:
a) at least one of the at least one first resonator element defines a first resonator element longitudinal axis and the at least one second resonator element defines a second resonator element longitudinal axis,
and
b) the at least one first injection element and the at least one second injection element are arranged or formed coaxially to one another.

### Claim 5 (depends on 1)

The injector device in accordance with claim 1, wherein at least one of:
a) at least one of the at least one first flushing channel defines a first flushing channel longitudinal axis, and
the at least one second flushing channel defines a second flushing channel longitudinal axis,
and
b) at least one of a first flushing channel cross-sectional area defined by the at least one first flushing channel is smaller than a first resonator channel cross-sectional area defined by the first resonator channel, and
a second flushing channel cross-sectional area defined by the at least one second flushing channel is smaller than a second resonator channel cross-sectional area defined by the second resonator channel.

### Claim 6 (depends on 1)

The injector device in accordance claim 1, wherein at least one of:
a) at least one of the at least one first resonator element and the at least one second resonator element is configured in the form of a Helmholtz resonator or in the form of a λ/4 resonator,
and
b) at least one of the at least one first resonator element is associated with at least one first injection element and the at least one second resonator element is associated with at least one second injection element.

### Claim 7 (depends on 1)

The injector device in accordance with claim 1, wherein the injector device comprises at least one of a plurality of first injection elements and a plurality of second injection elements.

### Claim 8 (depends on 1)

The injector device in accordance with claim 1, wherein at least one of:
a) the at least one first resonator element is arranged or formed in the region of an inlet of the at least one first injection element facing in the direction toward the first collection space,
and
b) the at least one second resonator element is arranged or formed in the region of an inlet of the at least one second injection element facing in the direction toward the second collection space.

### Claim 9 (depends on 1)

The injector device in accordance with claim 1, wherein the injector device comprises a first injector plate and a second injector plate, wherein at least one of:
a) the at least one first resonator elements are arranged or formed in the first injector plate,
and
b) the at least one second resonator elements are arranged or formed in the second injector plate.

### Claim 10 (depends on 9)

The injector device in accordance with claim 9, wherein at least one of:
a) the first injector plate and the second injector plate are arranged or formed in parallel to one another,
and
b) the second collection space is arranged or formed between the first injector plate and the second injector plate,
and
c) the first injector plate is configured in the form of a throttle plate and wherein a first throttle element is associated with the at least one first injection element in the region of the inlet thereof, said throttle element defining a smaller flow cross section than the at least one first injection element, and wherein the first throttle element is arranged or formed in or on the throttle plate.

### Claim 11 (depends on 1)

The injector device in accordance with claim 1, wherein the at least one first injection element is arranged on a plate-shaped injector element holder and is configured in the form of an injector sleeve.

### Claim 12 (depends on 11)

The injector device in accordance with claim 11, wherein the injector element holder on the one hand abuts in surface-to-surface contact against the first injector plate and on the other hand delimits the second collection space.

### Claim 13 (depends on 1)

The injector device in accordance with claim 1, wherein the at least one second injection element is arranged or formed on or in an injection head.

### Claim 14 (depends on 1)

The injector device in accordance with claim 1, wherein the at least one second injection element tapers in cross section in a single stage to form a second throttle element.

### Claim 15

An engine device for at least one of an aircraft and a spacecraft, which engine device comprises a combustion chamber with a nozzle and comprises an injector device arranged opposite the nozzle, wherein the injector device is configured for introducing a fluidic fuel and a fluidic oxidizing agent into the combustion chamber, which injector device defines a longitudinal axis and comprises at least one first injection element, which is configured in the form of a first fluid channel for fluidically connecting a first collection space for the fluidic oxidizing agent and the combustion chamber, and at least one second injection element, which is configured in the form of a second fluid channel for fluidically connecting a second collection space for the fluidic fuel and the combustion chamber,
wherein at least one of at least one first resonator element is associated with the at least one first injection element and wherein at least one second resonator element is associated with the at least one second injection element, and
wherein at least one of the at least one first resonator element is adapted to an eigenfrequency of the associated at least one first injection element and the at least one second resonator element is adapted to an eigenfrequency of the associated at least one second injection element,
wherein at least one of:
the at least one first resonator element and the first collection space are fluidically connected to one another by way of a first flushing channel, so that the fluid flowing through the at least one first injection element also flows at a flow speed through the at least one first resonator element, thereby ensuring that the same conditions prevail in the at least one first resonator element at any one time as in the at least one first injection element to be dampened, and
the at least one second resonator element and the second collection space are fluidically connected to one another by way of a second flushing channel, so that the fluid flowing through
the at least one second injection element also flows at a flow speed through the at least one second resonator element, thereby ensuring that the same conditions prevail in the at least one second resonator element at any one time as in the at least one second injection element to be dampened.

### Claim 16 (depends on 15)

The engine device in accordance with claim 15, wherein at least one of:
a) the engine device is configured in the form of a rocket engine,
and
b) the combustion chamber comprises a face wall opposite the nozzle and at least part of the injector device is arranged or formed in the face wall,
and
c) the engine device comprises at least one collection space, which is delimited by a collection space face wall.

### Claim 17

An aircraft or spacecraft with an engine device and a fuel tank for accommodating a fluidic fuel, wherein the engine device comprises a combustion chamber with a nozzle and comprises an injector device arranged opposite the nozzle, wherein the injector device is configured for introducing the fluidic fuel and a fluidic oxidizing agent into the combustion chamber, which injector device defines a longitudinal axis and comprises at least one first injection element, which is configured in the form of a first fluid channel for fluidically connecting a first collection space for the fluidic oxidizing agent and the combustion chamber, and at least one second injection element, which is configured in the form of a second fluid channel for fluidically connecting a second collection space for the fluidic fuel and the combustion chamber,
wherein at least one of at least one first resonator element is associated with the at least one first injection element and at least one second resonator element is associated with the at least one second injection element, and
wherein at least one of the at least one first resonator element is adapted to an eigenfrequency of the associated at least one first injection element and the at least one second resonator element is adapted to an eigenfrequency of the associated at least one second injection element,
wherein at least one of:
the at least one first resonator element and the first collection space are fluidically connected to one another by way of a first flushing channel, so that the fluid flowing through the at least one first injection element also flows at a flow speed through the at least one first resonator element, thereby ensuring that the same conditions prevail in the at least one first resonator element at any one time as in the at least one first injection element to be dampened, and
the at least one second resonator element and the second collection space are fluidically connected to one another by way of a second flushing channel, so that the fluid flowing through the at least one second injection element also flows at a flow speed through the at least one second resonator element, thereby ensuring that the same conditions prevail in the at least one second resonator element at any one time as in the at least one second injection element to be dampened.

### Claim 18 (depends on 17)

The aircraft or spacecraft in accordance with claim 17, wherein at least one of:
a) the fuel tank is configured to accommodate liquid hydrogen or liquid methane
and
b) the aircraft or spacecraft comprises an oxidizing agent tank for accommodating a fluidic oxidizing agent.

### Claim 19

A method for operating an engine device, in which method a fluidic fuel and a fluidic oxidizing agent are introduced with an injector device into a combustion chamber of the engine device, which injector device comprises at least one first injection element for fluidically connecting a first collection space for the fluidic oxidizing agent and the combustion chamber, and at least one second injection element for fluidically connecting a second collection space for the fluidic fuel and the combustion chamber, wherein at least one of acoustic natural vibrations in the at least one first injection element and/or that acoustic natural vibrations in the at least one second injection element are dampened,
wherein at least one of at least one first resonator element is associated with the at least one first injection element and at least one second resonator element is associated with the at least one second injection element, and wherein at least one of the at least one first resonator element is adapted to an eigenfrequency of the associated at least one first injection element and the at least one second resonator element is adapted to an eigenfrequency of the associated at least one second injection element,
wherein at least one of:
the at least one first resonator element and the first collection space are fluidically connected to one another by way of a first flushing channel, so that the fluid flowing through the at least one first injection element also flows at a flow speed through the at least one first resonator element, thereby ensuring that the same conditions prevail in the at least one first resonator element at any one time as in the at least one first injection element to be dampened, and
the at least one second resonator element and the second collection space are fluidically connected to one another by way of a second flushing channel, so that the fluid flowing through the at least one second injection element also flows at a flow speed through the at least one second resonator element, thereby ensuring that the same conditions prevail in the at least one second resonator element at any one time as in the at least one second injection element to be dampened.