AU2023222918A1 - Liquid Fuel Supply System Including Auxiliary Air Supply Device - Google Patents
Liquid Fuel Supply System Including Auxiliary Air Supply Device Download PDFInfo
- Publication number
- AU2023222918A1 AU2023222918A1 AU2023222918A AU2023222918A AU2023222918A1 AU 2023222918 A1 AU2023222918 A1 AU 2023222918A1 AU 2023222918 A AU2023222918 A AU 2023222918A AU 2023222918 A AU2023222918 A AU 2023222918A AU 2023222918 A1 AU2023222918 A1 AU 2023222918A1
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- AU
- Australia
- Prior art keywords
- air
- chamber
- turbine
- liquid fuel
- compressor
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 239000000446 fuel Substances 0.000 title claims abstract description 82
- 239000007788 liquid Substances 0.000 title claims abstract description 65
- 238000002156 mixing Methods 0.000 claims abstract description 28
- 238000002485 combustion reaction Methods 0.000 claims abstract description 20
- 230000035939 shock Effects 0.000 claims abstract description 11
- 239000002828 fuel tank Substances 0.000 claims description 11
- 238000007599 discharging Methods 0.000 claims description 6
- 238000009834 vaporization Methods 0.000 abstract description 5
- 230000008016 vaporization Effects 0.000 abstract description 5
- 238000000926 separation method Methods 0.000 abstract description 3
- 230000002708 enhancing effect Effects 0.000 abstract description 2
- 239000007789 gas Substances 0.000 description 5
- 238000001816 cooling Methods 0.000 description 3
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 2
- 239000004215 Carbon black (E152) Substances 0.000 description 2
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 229930195733 hydrocarbon Natural products 0.000 description 2
- 150000002430 hydrocarbons Chemical class 0.000 description 2
- 239000001257 hydrogen Substances 0.000 description 2
- 229910052739 hydrogen Inorganic materials 0.000 description 2
- 230000001965 increasing effect Effects 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 235000015842 Hesperis Nutrition 0.000 description 1
- 235000012633 Iberis amara Nutrition 0.000 description 1
- 239000001307 helium Substances 0.000 description 1
- 229910052734 helium Inorganic materials 0.000 description 1
- SWQJXJOGLNCZEY-UHFFFAOYSA-N helium atom Chemical compound [He] SWQJXJOGLNCZEY-UHFFFAOYSA-N 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 229910052757 nitrogen Inorganic materials 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D37/00—Arrangements in connection with fuel supply for power plant
- B64D37/34—Conditioning fuel, e.g. heating
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/22—Fuel supply systems
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/32—Arrangement, mounting, or driving, of auxiliaries
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/12—Plants including a gas turbine driving a compressor or a ducted fan characterised by having more than one gas turbine
-
- 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
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
- F02K9/46—Feeding propellants using pumps
-
- 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
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
- F02K9/605—Reservoirs
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
- B64D2033/0253—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of aircraft
- B64D2033/026—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of aircraft for supersonic or hypersonic aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Feeding, Discharge, Calcimining, Fusing, And Gas-Generation Devices (AREA)
- Nozzles (AREA)
- Fuel-Injection Apparatus (AREA)
- Feeding And Controlling Fuel (AREA)
- Jet Pumps And Other Pumps (AREA)
Abstract
The present invention relates to a liquid fuel supply system
including an auxiliary air supply device, and more specifically,
to a liquid fuel supply system including an auxiliary air supply
5 device with a fuel-air premixing section for receiving and
utilizing the necessary air from a main duct, allowing for
continuous and combustion-efficient operation. A liquid fuel
supply system including an auxiliary air supply device according
to the present invention is provided with a chamber that mixes
10 liquid fuel and hot air, which improves the insufficient time
available for vaporization and mixing of the liquid fuel due to
the high internal flow velocity of the combustion chamber in
supersonic aircraft, thereby enhancing the fuel vaporization
performance. Furthermore, according to the present invention, the
15 discharged air of the supplied auxiliary air is located at the
position where oblique shock waves hit, which eliminates the
oblique shock waves, allowing for the reduction of flow separation
and improving the starting characteristics of the inlet.
20
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FIGC2
Description
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FIGC2
[0001] The present application claims priority to Korean Patent
Application No. 10-2022-0127677, filed October 6, 2022, the
entire contents of which is incorporated herein for all purposes
by this reference.
Field of the Invention
[0002] The present invention relates to a liquid fuel supply
system including an auxiliary air supply device, and more
specifically, to a liquid fuel supply system including an
auxiliary air supply device with a fuel-air premixing section for
receiving and utilizing the necessary air, allowing for
continuous and combustion-efficient operation.
Description of the Related Art
[0003] The propulsion system of guided weapons can be broadly
divided into rockets and air-breathing engines. Air-breathing
engines primarily utilize liquid fuel and go through a process
of increasing enthalpy by combusting the ingested air and liquid fuel, which requires pre-combustion processes of injection, mixing, and vaporization of the liquid fuel inside the combustion chamber.
[0004] However, in the case of high-speed propulsion systems,
the short residence time of air inside the combustion chamber
makes it challenging to achieve efficient combustion, and
therefore, various technologies are being developed to overcome
this issue.
[0005] However, when using liquid hydrogen as the energy source,
utilizing highly reactive hydrogen in its liquid state can achieve
effective cooling of the gas and efficient combustion, but it
poses challenges as an energy source for guided weapons due to
its low energy density and poor storability.
[0006] Furthermore, when using liquid hydrocarbon fuels as the
energy source, the liquid hydrocarbon fuel in its liquid state
mainly relies on turbo pumps to pressurize and feed the fuel, and
it requires a separate pressurization source (such as helium tanks,
nitrogen, gas generators, etc.) for driving the turbo pumps. In
this case, the operating time of the pressurization source is
determined by the tank size or the capacity of the gas generator,
and since the capacity of the relevant device should vary based
on the flight distance, there is an issue where a smaller capacity
would limit the flight distance, while a larger capacity would
lead to increased weight, presenting a drawback.
[0007] Therefore, various technologies are being developed to improve continuous operation and combustion efficiency compared to the conventional fuel supply systems.
[0008] In Japanese Registered Patent Publication No. 5016356,
the combustion efficiency is improved by continuously supplying
air to the inlet of a compressor of a gas turbine engine.
[0009] In Japanese Patent Publication No. 2006-194247, the
combustion efficiency is improved by equipping a propulsion gas
turbine engine with a core engine assembly.
[0010] In Japanese Patent Publication No. 2006-336652, the
combustion efficiency is improved by controlling the airflow to
the auxiliary engine from the propulsion engine using an
adjustable valve that adjusts a portion of the inflowing air flow
into the propulsion engine.
[0011] Although these patent documents intend to enhance
combustion efficiency by incorporating additional engines or
maintaining a continuous air supply, the issue of short residence
time of air inside the combustion chamber still remains.
[0012] The present invention aims to solve the above problems by
including a pre-process in which fuel and air are injected, mixed,
and vaporized by a fuel-air premixing section, allowing for
continuity of combustion and improvement of combustion efficiency
through continuous utilization of the required air.
[0013] In order to accomplish the above object, a liquid fuel supply system including an auxiliary air supply device for a high speed aircraft according to the present invention may include a first chamber intaking external air and moves the intaken air to a compressor and a first turbine being driven by a portion of the intaken air from the first chamber, wherein the first turbine drives the compressor, and the air compressed by the compressor is mixed with liquid fuel.
[0014] Here, the compressor and the first turbine are connected
on the same axis.
[0015] In addition, the liquid fuel supply system including an
auxiliary air supply device for a high-speed aircraft according
to the present invention may include a first chamber intaking
external air and moving the intaken air to a compressor, a first
turbine being driven by a portion of the intaken air from the
first chamber, and a compressor driven by the first turbine,
wherein the air compressed by the compressor and liquid fuel are
mixed. Here, the intaken air means an air inflow introduced into
the first chamber from outside.
[0016] Here, the compressor and the first turbine are connected
on the same axis.
[0017] In addition, the liquid fuel supply system including the
auxiliary air supply device according to the present invention
may further include a second chamber intaking the external air
and moving the intaken air to a second turbine and a pump
supplying the liquid fuel from a fuel tank, wherein the second turbine is driven using the intaken air from the second chamber.
[0018] Here, the pump and the second turbine are connected on
the same axis.
[0019] In addition, the liquid fuel supply system including the
auxiliary air supply device according to the present invention
may further include a mixing chamber mixing the compressed air
and the liquid fuel and a combustion chamber into which the
compressed air and liquid fuel mixed in the mixing chamber are
injected.
[0020] In addition, the liquid fuel supply system including the
auxiliary air supply device according to the present invention
may further include a first air duct connecting the first chamber
and the compressor and moving the intaken air from the first
chamber and a second air duct connecting the second chamber and
the second turbine and moving the intaken air from the second
chamber.
[0021] In addition, the liquid fuel supply system including the
auxiliary air supply device according to the present invention
may further include a first compressed air duct connecting the
compressor and the mixing chamber and moving the air compressed
by the compressor to the mixing chamber and a second compressed
air duct connected to the first turbine and branched off from the
first compressed air duct to move a portion of the air compressed
by the compressor to the first turbine.
[0022] Here, the second compressed air duct may comprises a control valve, which regulates the amount of the compressed air moving from the compressor to the first turbine.
[0023] In addition, the liquid fuel supply system including the
auxiliary air supply device according to the present invention
may further include a first fuel duct connecting the fuel tank
and the pump and moving the liquid fuel from the fuel tank to the
pump and a second fuel duct connecting the pump and the mixing
chamber and moving the liquid fuel from the pump.
[0024] In addition, the first chamber cancels the oblique shock
wave generated by the movement of the high-speed aircraft suppress
flow separation caused by the flow shock waves.
[0025] In addition, the second chamber may include a guide vane
adjustable in angle.
[0026] In addition, the first turbine may include a first cooled
air duct discharging the air used for driving to the outside, and
the second turbine may include a second cooled air duct
discharging the air used for driving to the outside.
[0027] FIG. 1 illustrates a high-speed aircraft to which a liquid
fuel supply system including the auxiliary air supply device
according to the present invention is applied; and
[0028] FIG. 2 illustrates a liquid fuel supply system including
the auxiliary air supply device according to the present invention.
[0029] The present invention can be modified in various ways and
may have several embodiments; therefore, specific embodiments are
illustrated in the drawings and are described in detail for a
more concrete explanation. However, this is not intended to limit
the present invention to specific embodiments, and it should be
understood that all modifications, equivalents, and substitutions
fall within the scope and spirit of the present invention.
[0030] As used herein, terms including an ordinal number such as
"first" and "second" can be used to describe various components
without limiting the components.
[0031] These terms are used only for distinguishing one component
from another component.
[0032] Hereinafter, a description is made of the liquid fuel
supply system including the auxiliary air supply device according
to an embodiment of the present invention with reference to
accompanying drawings.
[0033] FIG. 1 illustrates a high-speed aircraft to which a liquid
fuel supply system including the auxiliary air supply device
according to the present invention is applied.
[0034] FIG. 2 illustrates a liquid fuel supply system including
the auxiliary air supply device according to the present invention.
[0035] Although a high-speed aircraft 1 is representatively
depicted in FIG. 1, it is obvious to those skilled in the art
that this represents merely one embodiment of the present invention and all types of aircraft, including supersonic aircraft, fall within the scope of the present invention.
[0036] In addition, FIG. 2 shows a cross-section taken along the
line A-A' in FIG. 1.
[0037] As shown in FIG. 2, the liquid fuel supply system
including the auxiliary air supply device according to the present
invention is used in a high-speed aircraft 1 and includes a first
chamber 10a that intakes external air and moves the intaken air
to a compressor 20, a first turbine 30a driven by a portion of
the air intaken from the first chamber 10a, and the compressor
20 driven by the first turbine 30a, wherein the compressed air
from the compressor 20 is mixed with liquid fuel.
[0038] Here, the compressor 20 and the first turbine 30a are
connected on the same axis.
[0039] That is, a portion of the air intaken from the first
chamber 10a drives the first turbine 30a, and this first turbine
30a in turn drives the compressor 20, causing the air sucked into
the compressor 20 to be compressed, resulting in an increase in
pressure and temperature.
[0040] In more detail, the power of the first turbine 30a is
generated by the difference between the pressure at the aft end
of the compressor 20 and the pressure of the external air pressure
at the aft end of the first cooled air duct 35a.
[0041] Preferably, the liquid fuel supply system including the
auxiliary air supply device according to the present invention further includes a first air duct 15a connecting the first chamber
10a and the compressor 20, allowing the air intaken from the first
chamber 10a to move.
[0042] That is, the pressure difference between the first chamber
10a and the external air causes the air intaken through the first
air duct 15a to move towards the compressor 20, and a portion of
the intaken air acts as the driving force that generates the power
of the first turbine 30a.
[0043] The liquid fuel supply system including the auxiliary air
supply device according to the present invention further includes
a second chamber 10b that intakes external air and moves the
intaken air to the second turbine 30b, and a pump 40 that supplies
liquid fuel from the fuel tank 50, wherein the second turbine 30b
is driven using the air intaken from the second chamber 10b.
[0044] Here, the pump 40 and the second turbine 30b are connected
on the same axis.
[0045] That is, the second turbine 30b is driven using the air
intaken from the second chamber 10b, and this second turbine 30b
in turn drives the pump 40 to move the liquid fuel.
[0046] In more detail, the power of the second turbine 30b is
generated by the difference in pressure between the second chamber
10b and the external air.
[0047] Preferably, the liquid fuel supply system including the
auxiliary air supply device according to the present invention
further includes a second air duct 15b connecting the second chamber 10b and the second turbine 30b, allowing the air intaken from the second chamber 10b to move.
[0048] That is, the pressure difference between the second
chamber 10b and the external air causes the air intaken through
the second air duct 15b to move towards the second turbine 30b,
and the intaken air acts as the driving force that generates the
power of the second turbine 30b.
[0049] In addition, the second chamber 10b may include a guide
vane 17, which increase the stagnation pressure in the second
chamber 10b and allow to enhance or control the power of the
second turbine 30b more effectively by varying its angle.
[0050] Preferably, the liquid fuel supply system including the
auxiliary air supply device according to the present invention
further includes a mixing chamber 60 where compressed air and
liquid fuel are mixed, and a fuel chamber 70 where the mixed
compressed air and liquid fuel are injected from the mixing
chamber 60.
[0051] Particularly, the fuel chamber 70 is an area that includes
a space where the mixed compressed air and liquid fuel are
injected, as shown in FIG. 2.
[0052] That is, the present invention is characterized by the
compressed air and liquid fuel being pre-mixed in the mixing
chamber 60 and then injected into the fuel chamber 70 in a mixed
state of compressed air and liquid fuel.
[0053] With reference to FIG. 2, a cowl tip 3 is provided in a pointed shape so as to generate oblique chock waves 4c as the high-speed aircraft 1 moves rapidly, and these generated oblique shock waves 4c reach and cancel out in the first chamber 10a.
[0054] An oblique shock wave occurs when the direction of the
free stream (indicated by the arrows) changes due to the shape
of the structure, and in FIG. 2, three cases of oblique shock
waves 4a, 4b, and 4c are illustrated; however, it is obvious to
those skilled in the art that various cases may arise depending
on the shape of the high-speed aircraft 1.
[0055] Here, the free stream refers to the flow of air entering
the engine of the high-speed aircraft 1.
[0056] Furthermore, as the high-speed aircraft 1 moves, a
streamline 5a may form in the free stream, and particularly, the
streamline 5b occurring at the aft end of the combustion chamber
70 represents the boundary region between the flame generated by
the combustion chamber and the free stream.
[0057] In this case, as shown in FIG. 2, the streamline 5a changes
direction when it encounters the oblique shock waves 4a, 4b, and
4c and ultimately forms parallel to the cowl tip 3.
[0058] Preferably, the liquid fuel supply system including the
auxiliary air supply device according to the present invention
includes a first compressed air duct 25a connecting the compressor
20 and the mixing chamber 60, allowing the compressed air from
the compressor 20 to move to the mixing chamber 60, and a second
compressed air duct 25b connected to the first turbine 30a and branching off from the first compressed air duct 25a to direct a portion of the compressed air from the compressor 20 to the first turbine 30a.
[0059] In more detail, the air intaken from the first chamber
10a is partially directed to the first compressed air duct 25a
and the second compressed air duct 25b and then moves to the first
turbine 30a, driving the first turbine 30a.
[0060] Furthermore, when the first turbine 30a driven by the
intaken air compresses the air within the compressor 20, causing
the compressed air's temperature and pressure to increase, and
the compressed air then moves to the mixing chamber 60 through
the first compressed air duct 25a.
[0061] In this case, not all of the compressed air moves to the
mixing chamber 60, but some of it moves to the first turbine 30a
through the second compressed air duct 25b branched off from the
first compressed air duct 25a to drive the first turbine 30a
again.
[0062] That is, not all of the compressed air moves to the mixing
chamber 60, but some of it moves to the first turbine 30a,
continuously driving the first turbine 30a, and as a result, the
compressor 20 keeps compressing the air continuously.
[0063] In this case, the second compressed air duct 25b may
include a control valve 27, which regulates the amount of
compressed air moving from the compressor 20 to the first turbine
30a
[0064] That is, the control valve (27) allows a larger amount of
air to move to the first turbine 30a when more airflow is required
for the first turbine 30a, and conversely, when less airflow is
needed for the first turbine 30a, more air moves to the mixing
chamber 60.
[0065] The liquid fuel supply system including the auxiliary air
supply device according to the present invention may further
include a first fuel duct 55a connecting the fuel tank 50 and the
pump 40 through which liquid fuel moves from the fuel tank 50 to
the pump 40, and a second fuel duct 55b connecting the pump 40
and the mixing chamber 60 through which liquid fuel moves from
the pump 40 to the mixing chamber 60.
[0066] That is, the liquid fuel may move from the fuel tank 50
to the pump 40 through the first fuel duct 55a, and when the
second turbine 30b is driven, the power generated by the second
turbine 30b causes the pump 40 to operate, enabling liquid fuel
to move from the pump 40 to the mixing chamber 60 through the
second fuel duct 55b.
[0067] Preferably, the first turbine 30a includes a first cooled
air duct 35a for discharging the air used for driving to the
outside, and the second turbine 30b includes a second cooled air
duct 35b for discharging the air used for driving to the outside.
[0068] That is, both the first and second turbines 30a and 30b
utilize air for propulsion, and the air used during the operation
loses energy through expansion while being cooled so as to be discharged to the outside through the first cooled air duct 35a and the second cooled air duct 35b, respectively.
[0069] In more detail, the cooled air is discharged to the
outside through the first discharge port 37a at the aft end of
the first cooling duct 35a and the second discharge port 37b at
the aft end of the second cooling duct 35b, and the air inflow
occurs particularly because the pressure at the intake side of
the first chamber 10a and the intake side of the second chamber
10b is greater than the pressure at the respective discharge ports
37a and 37b, enabling the air to flow in.
[0070] A liquid fuel supply system including an auxiliary air
supply device according to the present invention is provided with
a chamber that mixes liquid fuel and hot air, which improves the
insufficient time available for vaporization and mixing of the
liquid fuel due to the high internal flow velocity of the
combustion chamber in supersonic aircraft, thereby enhancing the
fuel vaporization performance.
[0071] Furthermore, according to the present invention, the
discharged air of the supplied auxiliary air is located at the
position where oblique shock waves hit, which eliminates the
oblique shock waves, allowing for the reduction of flow separation
and improving the starting characteristics of the inlet.
[0072] The embodiment illustrated in the drawings is intended
solely for the purpose of explaining the invention, and those
skilled in the art would understand that various modifications or equivalent embodiments are possible based on the detailed description of the invention.
[0073] In particular, although a high-speed aircraft was used as
an example for illustration, it is obvious to those skilled in
the art that any aircraft using a fuel supply system falls within
the scope of the present invention.
[0074] Therefore, the true scope of the present invention should
be determined based on the technical concept of the patent claims.
1: high-speed aircraft
2: lamp
3: cowl tip
10a: first chamber
10b: second chamber
15a: first air duct
15b: second air duct
17: guide vane
20: compressor
25: compressed air duct
25a: first compressed air duct
25b: second compressed air duct
27: control valve
30a: first turbine
30b: second turbine
35: cooled air duct
35a: first cooled air duct
35b: second cooled air duct
37a: first discharge port
37b: second discharge port
40: pump
50: fuel tank
55: fuel duct
55a: first fuel duct
55b: second fuel duct
60: mixing chamber
70: combustion chamber
Claims (14)
1. A liquid fuel supply system including an auxiliary air
supply device for a high-speed aircraft, the system comprising:
a first chamber intaking external air and moving the intaken
air to a compressor; and
a first turbine being driven by a portion of the intaken
air from the first chamber,
wherein the first turbine drives the compressor, and the
air compressed by the compressor is mixed with liquid fuel.
2. The system of claim 1, wherein the compressor and the
first turbine are connected on the same axis.
3. The system of claim 1, further comprising: a second
chamber intaking the external air and moving the intaken air to
a second turbine; and a pump supplying the liquid fuel from a
fuel tank, Wherein the second turbine is driven using the intaken
air from the second chamber.
4. The system of claim 3, wherein the pump and the second
turbine are connected on the same axis.
5. The system of claim 3, further comprising a mixing chamber
mixing the compressed air and the liquid fuel.
6. The system of claim 5, further comprising a combustion
chamber into which the compressed air and liquid fuel mixed in
the mixing chamber are injected.
7. The system of claim 1, further comprising a first air
duct connecting the first chamber and the compressor and moving
the intaken air from the first chamber.
8. The system of claim 3, further comprising a second air
duct connecting the second chamber and the second turbine and
moving the intaken air from the second chamber.
9. The system of claim 5, further comprising:
a first compressed air duct connecting the compressor and
the mixing chamber and moving the air compressed by the compressor
to the mixing chamber; and
a second compressed air duct connected to the first turbine
and branched off from the first compressed air duct to move a
portion of the air compressed by the compressor to the first
turbine.
10. The system of claim 9, wherein the second compressed
air duct comprises a control valve, which regulates the amount
of the compressed air moving from the compressor to the first
turbine.
11. The system of claim 5, further comprising:
a first fuel duct connecting the fuel tank and the pump and
moving the liquid fuel from the fuel tank to the pump; and
a second fuel duct connecting the pump and the mixing chamber
and moving the liquid fuel from the pump.
12. The system of claim 1, wherein the first chamber cancels
the oblique shock wave generated by the movement of the high
speed aircraft.
13. The system of claim 3, wherein the second chamber
comprises a guide vane adjustable in angle.
14. The system of claim 3, wherein the first turbine
comprises a first cooled air duct discharging the air used for
driving to the outside, and the second turbine comprises a second
cooled air duct discharging the air used for driving to the
outside.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| KR10-2022-0127677 | 2022-10-06 | ||
| KR1020220127677A KR102705171B1 (en) | 2022-10-06 | 2022-10-06 | Liquid Fuel Supply System Comprising Assisted Air Supply System |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| AU2023222918A1 true AU2023222918A1 (en) | 2024-05-02 |
Family
ID=90715777
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| AU2023222918A Pending AU2023222918A1 (en) | 2022-10-06 | 2023-08-31 | Liquid Fuel Supply System Including Auxiliary Air Supply Device |
Country Status (2)
| Country | Link |
|---|---|
| KR (1) | KR102705171B1 (en) |
| AU (1) | AU2023222918A1 (en) |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS5016356B1 (en) | 1969-02-18 | 1975-06-12 | ||
| US7549291B2 (en) | 2003-01-28 | 2009-06-23 | General Electric Company | Methods and apparatus for operating gas turbine engines |
| US7464533B2 (en) | 2003-01-28 | 2008-12-16 | General Electric Company | Apparatus for operating gas turbine engines |
| EP2932068B1 (en) * | 2012-12-13 | 2017-11-15 | United Technologies Corporation | Gas turbine engine with cooling scheme for drive gear system and pitch control |
-
2022
- 2022-10-06 KR KR1020220127677A patent/KR102705171B1/en active IP Right Grant
-
2023
- 2023-08-31 AU AU2023222918A patent/AU2023222918A1/en active Pending
Also Published As
| Publication number | Publication date |
|---|---|
| KR102705171B1 (en) | 2024-09-11 |
| KR20240048194A (en) | 2024-04-15 |
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