CN115075953A - Fuel supply flow passage, injection device, supply system, engine, and aircraft - Google Patents
Fuel supply flow passage, injection device, supply system, engine, and aircraft Download PDFInfo
- Publication number
- CN115075953A CN115075953A CN202210856744.8A CN202210856744A CN115075953A CN 115075953 A CN115075953 A CN 115075953A CN 202210856744 A CN202210856744 A CN 202210856744A CN 115075953 A CN115075953 A CN 115075953A
- Authority
- CN
- China
- Prior art keywords
- liquid phase
- phase branch
- channel
- fuel
- component
- 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
Images
Classifications
-
- 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
- F02C7/222—Fuel flow conduits, e.g. manifolds
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Fuel-Injection Apparatus (AREA)
Abstract
The invention relates to a fuel supply channel, an injection device, a supply system, a continuous rotary detonation engine and an aircraft. The technical problem to be solved is that the diffusion, crushing and atomization degrees and the circumferential distribution uniformity of the liquid phase fuel are not good enough. The fuel supply flow passage may be provided with a liquid phase flow passage assembly and a vapor phase flow passage assembly. The liquid phase flow channel sub-components comprise liquid phase main channels and branch channels. The outlet of each liquid phase branch channel is smaller than the liquid phase branch channel. The axes of all the cylindrical holes at the rear section of the gas-phase branch channels which are uniformly distributed in the circumferential direction are intersected at a point. The total number of the liquid phase branch passages is the same as that of the gas phase branch passages, and the liquid phase branch passages and the gas phase branch passages are in one-to-one correspondence. The partial cylindrical outer wall surface of each liquid phase branch channel partially extends into the corresponding rear section cylindrical hole of the gas phase branch channel and forms a coaxial relationship. The technical means that a plurality of liquid phase fuel channels are distributed uniformly in the circumferential direction, and the liquid phase fuel of each channel and the oxidant form coaxial injection respectively are adopted, so that the technical effects of improving the mixing uniformity and circumferential uniformity of the combustible mixture are achieved.
Description
Technical Field
The invention relates to a fuel supply channel, a fuel injection device, a fuel supply system, a continuous rotation detonation engine, and an aircraft using the continuous rotation detonation engine.
Background
The most relevant documents to the present invention are, document 1: a rotary detonation engine experimental device, Chinese invention patent, application No. 201510055761.1; document 2: bykovskii, F.A., ZHdan, S.A. & Vedernikov, E.F. continuos destination of the Liquid Kerosene-Air Mixture with Addition of Hydrogen or Syngas [ J ], Combustion, expansion, and Shock Waves, 2019, 55(5): 589-; document 3: jan Kindracki, Experimental research on relating destination in liquid fuel-gas air mix [ J ], Aerospace Science and Technology, 2015, 43: 445-453. In the prior art, the main objective is to expect improved mixing uniformity and circumferential uniformity of the combustible mixture; the main technical characteristics of the structure are that 4 to 8 cylindrical fuel channels are arranged on the outer wall of a cylindrical combustion chamber in the circumferential direction, and oxidant flowing at high speed collides against fuel at the outlet of each cylindrical fuel channel; the main effect is that a limited area near the point of impact of the fuel with the oxidant can create local diffusion of the fuel and local mixing with the oxidant. In the process of implementing the invention, the inventor finds that at least the following problems exist in the prior art: when liquid fuel is used, i.e. the fuel exists in liquid phase at the upstream of the channel outlet, the fuel has poor diffusion, crushing and atomization at the downstream of the channel outlet, and the fuel has poor distribution uniformity in the circumferential direction.
Disclosure of Invention
The technical problems to be solved by the invention are as follows: the liquid phase fuel has poor diffusion, fragmentation, atomization and circumferential distribution uniformity.
In order to solve the above technical problems, the present invention adopts the following specific technical solutions.
The fuel supply flow channel according to the first aspect of the present invention may be provided with a liquid phase flow channel assembly and a vapor phase flow channel assembly. The liquid phase flow channel assembly includes two or more liquid phase flow channel sub-members. All the liquid phase flow channel sub-components have the same structure. Each liquid phase flow channel sub-component comprises a liquid phase main channel and two or more liquid phase branch channels.
Each liquid trunk has one or more liquid trunk inlets. The outer wall surface of each liquid phase branch channel is locally cylindrical. Each liquid phase branch passage is provided with a liquid phase branch passage outlet. The flow cross-sectional area of the outlet of each liquid phase branch passage is smaller than that of each liquid phase branch passage. The flow cross section areas of all liquid phase branch outlets are equal.
The gas phase runner component comprises a gas phase main channel and two or more gas phase branch channels. The gas trunk has one or more gas trunk inlets. Each gas phase branch channel is provided with a gas phase branch channel front section, a gas phase branch channel rear section and a gas phase branch channel outlet. The rear section of each gas phase branch channel is a cylindrical hole. The axes of the cylindrical holes at the rear section of all the gas phase branch passages are intersected at a point. All the cylindrical holes at the rear section of the gas-phase branch passage are uniformly and circumferentially distributed.
The total number of the liquid phase branch passages is the same as that of the gas phase branch passages, and the liquid phase branch passages and the gas phase branch passages are in one-to-one correspondence. The total number of the liquid phase branch passage outlets and the total number of the gas phase branch passage outlets are the same and are in one-to-one correspondence. The total number of liquid phase branch outlets is greater than or equal to 12.
The diameter of the local cylindrical outer wall surface of each liquid phase branch passage is smaller than that of the cylindrical hole at the rear section of the corresponding gas phase branch passage. The partial cylindrical outer wall surface of each liquid phase branch channel partially extends into the corresponding cylindrical hole at the rear section of the gas phase branch channel. The axial line of the local cylindrical outer wall surface of each liquid phase branch channel and the axial line of the cylindrical hole at the rear section of the corresponding gas phase branch channel form a coaxial relationship.
The fuel injection device according to the second aspect of the present invention may include a fuel flow on/off actuating member and the fuel supply flow passage according to the first aspect. The number of the fuel flow on-off executing components is the same as the total number of the liquid-phase trunk inlet, the fuel flow on-off executing components and the liquid-phase trunk inlet are in one-to-one correspondence, and each corresponding fuel flow on-off executing component and the liquid-phase trunk inlet are in high hydraulic sealing fit.
The fuel supply system according to the third aspect of the present invention may include a fuel storage member, a fuel pressure increasing member, and a fuel injection member. The fuel storage component and the fuel pressurizing component are connected by a pipeline, and the fuel pressurizing component and the fuel injection component are connected by a pipeline. Wherein the fuel injection component is the fuel injection device of the foregoing second aspect.
The continuous rotary detonation engine according to the fourth aspect of the present invention may include a fuel supply member, a combustion chamber member, and an ignition member. The fuel supply part and the combustion chamber part are connected by a pipeline, and the detonation part extends into the combustion chamber part through a hole on the outer wall surface of the shell of the combustion chamber part. Wherein the fuel supply means is the fuel supply system of the aforementioned third aspect. The fuel supply flow channel is communicated with the outer wall surface of the shell of the combustion chamber component by adopting a connecting piece, and is fastened and sealed at high pressure.
The aircraft according to the fifth aspect of the present invention may include an engine component, a control component, and a load component. The engine component and the control component are connected through a communication data line, the load component comprises an aircraft shell and a filler, and the filler, the control component and the engine component are sequentially arranged at upper, middle and lower positions in the aircraft shell. Wherein the engine component is the continuous rotation detonation engine of the fourth aspect described above.
One of the above technical solutions has the following advantages or beneficial effects:
in the fuel supply flow channel related to the first aspect of the invention, the technical means that the liquid phase fuel channels are distributed in a large number and uniformly distributed in the circumferential direction and the liquid phase fuel in each channel and the oxidant form coaxial injection are adopted, so that the technical problems of poor diffusion, crushing and atomization degree and poor circumferential distribution uniformity of the liquid phase fuel are solved, and the technical effects of improving the mixing uniformity and circumferential uniformity of the combustible mixture are achieved. In the aspect of concrete quantification, the Sott average diameter index of liquid drops under the constant flow condition of 60MPa pressure difference of liquid-phase aviation fuel can be improved to 45 micrometers, and the circumferential uniformity can be improved to more than 1.5 times.
The fuel injection device according to the second aspect of the present invention includes the fuel supply channel according to the first aspect, and therefore has the technical effect of the fuel supply channel. And the Sott average diameter index of liquid drops under the condition of 180MPa pressure difference single-injection flow of the liquid-phase aviation fuel can be improved to 25 micrometers.
The fuel supply system according to the third aspect of the present invention includes the fuel supply flow passage according to the first aspect, and therefore has the technical effect of the fuel supply flow passage. And the Sott average diameter index of liquid drops under the condition of single or multiple or constant jet flow under the 180MPa pressure difference of the liquid-phase aviation fuel can be improved to 25 micrometers.
The continuous rotary detonation engine according to the fourth aspect of the invention has the fuel supply flow passage of the first aspect described above, and has the technical effects of the fuel supply flow passage, wherein the improvement in the uniformity of mixing of the combustible mixture can improve the combustion efficiency, and wherein the improvement in the uniformity of the combustible mixture in the circumferential direction can improve the combustion stability. And the defect that the liquid phase fuel needs to be ignited by the aid of gas phase fuel in the prior art is overcome, and the technical effect that continuous rotary detonation combustion can be formed only by using the liquid phase fuel is achieved.
The aircraft according to a fifth aspect of the present invention is provided with the fuel supply flow path of the first aspect described above, and therefore has the technical effects of a fuel supply flow path in which improvement in the uniformity of mixing of a combustible mixture can improve thrust and mach number, and in which improvement in the circumferential uniformity of a combustible mixture can improve flight stability. And the complexity that an auxiliary gas phase fuel system needs to be configured in the aircraft adopting the liquid phase fuel continuous rotation detonation engine in the prior art is overcome, and the technical effects of improving the working reliability and the volume energy density are achieved.
Drawings
FIG. 1 is a relational diagram of an embodiment of several aspects of the invention.
Fig. 2A is a schematic structural view (section a) of an embodiment of a fuel supply flow passage according to the present invention.
Fig. 2B is a schematic structural view (partial detail of the section a) of an embodiment of the fuel supply flow channel relating to the present invention.
Fig. 3 is a schematic structural view (partial detail of the section B) of an embodiment of a fuel supply flow channel relating to the present invention.
Fig. 4 is a schematic view (section a) of a seal structure of an embodiment of a fuel injection device relating to the present invention.
FIG. 5 is a schematic illustration of a coupling configuration for an embodiment of a continuous rotary detonation engine to which the present invention relates.
Description of the symbols
100 fuel supply flow passage
120 liquid phase flow passage sub-piece
130 liquid phase trunk road
132 liquid phase main channel inlet
140 liquid phase branch channel
142 partial cylindrical outer wall surface
144 liquid phase branch outlet
160 gas phase main duct
170 gas phase branch channel
172 gas phase branch front section
174 gas-phase branch passage rear section
176 gas phase branch outlet
178 gas phase branch passage rear section cylindrical hole
190 fuel flow on-off actuating member
200 fuel injection device
210 inner conical surface-spherical crown surface sealing matching A
300 fuel supply system
320 fuel storage component
340 fuel pressurizing unit
360 fuel injection component
400 continuous rotation detonation engine
420 fuel supply unit
440 combustion chamber component
442 casing outer wall surface
444 screw fitting A
446 Metal pad A
460 detonation component
500 aircraft
520 Engine component
540 control unit
560 a load member.
Detailed Description
As shown in fig. 1, the relationship between the embodiments of the aspects of the present invention is illustrated, and the embodiments of the aspects of the present invention are in a serial arrangement.
As shown in fig. 2A and 2B with associated partial detail, an embodiment of a fuel supply flowpath 100 in accordance with a first aspect of the present invention may be provided with a liquid phase flowpath assembly and a vapor phase flowpath assembly.
The liquid phase flow channel assembly includes two or more liquid phase flow channel sub-members 120, all of the liquid phase flow channel sub-members 120 being identical in structure. Each liquid phase flow channel sub-member 120 includes one liquid phase trunk 130, two or more liquid phase branches 140.
Each liquid trunk 130 has one or more liquid trunk inlets 132. The liquid trunk 130 may be: the central line shapes of all the liquid phase main channels 130 are circular arc shapes, the central line circular arc radiuses of all the liquid phase main channels 130 are equal, the sum of the central line circular arc radians of all the liquid phase main channels 130 is less than or equal to 2 pi, all the liquid phase main channels 130 are uniformly distributed in the circumferential direction, the flow cross section of each liquid phase main channel 130 is circular, and the flow cross section area of each liquid phase main channel 130 is less than or equal to 4 square millimeters.
The flow cross-sectional shape of each liquid phase branch 140 may be circular and the flow cross-sectional area may be less than or equal to 2 square millimeters. The outer wall surface of each liquid phase branch 140 has a partially cylindrical, partially cylindrical outer wall surface 142. Each liquid phase branch 140 has a liquid phase branch outlet 144. The flow cross-sectional area of each liquid phase branch outlet 144 is smaller than the flow cross-sectional area of each liquid phase branch 140. The flow cross-sectional areas of all the liquid phase branch outlets 144 are equal, and the flow cross-sectional area of each liquid phase branch outlet 144 is less than or equal to 0.2 square millimeters. The flow cross-sectional shape of each liquid phase branch outlet 144 may be circular.
As shown in fig. 3, the gas phase flow channel assembly includes a gas phase main channel 160, two or more gas phase branch channels 170. The gas trunk 160 has one or more gas trunk inlets. Each gas branch 170 has a gas branch front section 172, a gas branch rear section 174, and a gas branch outlet 176. The flow cross-sectional shape of each of the gas phase branch front sections 172 may be circular.
Each gas branch rear section 174 is a cylindrical bore, i.e., a gas branch rear section cylindrical bore 178. The axes of the cylindrical holes 178 at the rear section of all the gas phase branch channels meet at a point. All the gas phase branch passage rear section cylindrical holes 178 are uniformly distributed circumferentially.
The total number of liquid phase branches 140 and the total number of gas phase branches 170 are the same and correspond one to one. The total number of liquid phase branch outlets 144 and the total number of gas phase branch outlets 176 are the same and correspond one-to-one. The total number of liquid phase branch outlets 144 is greater than or equal to 12, and further the total number of liquid phase branch outlets 144 may be greater than or equal to 30.
The diameter of the partial cylindrical outer wall surface 142 of each liquid phase branch 140 is smaller than the diameter of the corresponding gas phase branch rear section cylindrical hole 178, and further, the difference between the diameter of the partial cylindrical outer wall surface 142 of each liquid phase branch 140 and the diameter of the corresponding gas phase branch rear section cylindrical hole 178 is smaller than or equal to 4 mm. The partially cylindrical outer wall 142 of each liquid phase branch 140 extends partially into the corresponding gas phase branch rear section cylindrical bore 178. The axis of the partially cylindrical outer wall surface 142 of each liquid phase branch 140 is in coaxial relationship with the axis of the corresponding gas phase branch rear section cylindrical bore 178. The geometric center of each corresponding liquid phase branch outlet 144 may be coincident with the geometric center of the vapor phase branch outlet 176.
The whole set of liquid phase flow channel assembly has the structural strength of bearing the internal hydraulic pressure of more than or equal to 30MPa and high hydraulic tightness. Further, the whole set of liquid phase flow channel assembly has structural strength for bearing internal hydraulic pressure of 180MPa or more and high hydraulic tightness.
The embodiment can achieve the following technical effects: because the technical means that a plurality of circumferentially and uniformly distributed liquid-phase fuel channels are arranged and the liquid-phase fuel of each channel and the oxidant form coaxial injection is adopted, the technical problems of poor diffusion, crushing and atomization degree and circumferential distribution uniformity of the liquid-phase fuel are solved, and the technical effects of improving the mixing uniformity and circumferential uniformity of the combustible mixture are further achieved. In the aspect of concrete quantification, the Sott average diameter index of liquid drops of the liquid-phase aviation fuel under the condition of constant flow at the pressure difference of 60MPa can be improved to 45 micrometers, and the circumferential uniformity can be improved to more than 1.5 times.
As shown in fig. 4, an embodiment of a fuel injection device 200 according to a second aspect of the present invention may include a fuel flow on/off actuating member 190 and the embodiment of the fuel supply flow path 100 according to the first aspect. The number of the fuel flow on-off performing parts 190 is the same as and corresponds to the total number of the liquid phase trunk inlets 132. Each of the corresponding fuel flow on-off actuating member 190 and the liquid phase main passage inlet 132 has a high hydraulic pressure sealing engagement with each other, an example of the sealing engagement may be an internal taper surface-spherical crown surface sealing engagement a210, and an example of the pressing force applied to the internal taper surface-spherical crown surface sealing engagement a210 may be a screw thread axial force of a screw. The embodiment of the fuel injection device 200 includes the embodiment of the fuel supply flow path 100, and therefore has the technical effects of the embodiment of the fuel supply flow path 100. And the Sott average diameter index of liquid drops under the condition of 180MPa pressure difference single-injection flow of the liquid-phase aviation fuel can be improved to 25 micrometers.
An embodiment of the fuel supply system 300 according to the third aspect of the present invention may include a fuel storage unit 320, a fuel pressure increasing unit 340, and a fuel injection unit 360. The fuel storage part 320 and the fuel pressurizing part 340 are connected by a pipeline, and the fuel pressurizing part 340 and the fuel injection part 360 are connected by a pipeline, wherein the pipeline can be a high-pressure oil pipe assembly which is common in the hydraulic industry, and the common high-pressure oil pipe assembly can be implemented by referring to the national mechanical industry standard JB/T12036-2015. Wherein the fuel injection component 360 is the fuel injection device 200 embodiment of the second aspect described above. The embodiment of the fuel supply system 300 includes the embodiment of the fuel supply flow channel 100, and therefore has the technical effect of the embodiment of the fuel supply flow channel 100. And the Sott average diameter index of liquid drops under the condition of single or multiple or constant jet flow under the 180MPa pressure difference of the liquid-phase aviation fuel can be improved to 25 micrometers.
An embodiment of the continuous rotary detonation engine 400 according to the fourth aspect of the present invention may include a fuel supply member 420, a combustion chamber member 440, and an ignition member 460. The fuel supply component 420 and the combustor component 440 are connected by a conduit, which may be a high pressure fuel line assembly as is common in the hydraulic industry. The ignition element 460 extends into the combustion chamber element 440 through a hole in the outer wall of the combustion chamber element 440. Wherein the fuel supply component 420 is the fuel supply system 300 embodiment of the third aspect described above. The fuel supply channel 100 is connected with the outer wall 442 of the housing of the combustor member 440 for communication, fastening and high pressure sealing; as shown in fig. 5, one fastening embodiment of the connector may be a screw fit a 444; as shown in fig. 3, one communicating and high pressure sealing embodiment of the connector may be metal gasket a 446. The continuous rotation detonation engine 400 embodiment having the fuel supply flow passage 100 embodiment has the technical effect of the fuel supply flow passage 100 embodiment, wherein the improvement in the homogeneity of the combustible mixture may improve combustion efficiency, and wherein the improvement in the circumferential homogeneity of the combustible mixture may improve combustion stability. And the defect that the liquid phase fuel needs to be ignited by the aid of gas phase fuel in the prior art is overcome, and the technical effect that continuous rotary detonation combustion can be formed only by using the liquid phase fuel is achieved.
An embodiment of the aircraft 500 according to the fifth aspect of the present invention may include an engine component 520, a control component 540, and a load component 560. The engine component 520 and the control component 540 are connected by communication data lines, and the load component 560 includes an aircraft housing and a filler, and the filler, the control component 540 and the engine component 520 are sequentially disposed at upper, middle and lower positions inside the aircraft housing. Wherein the engine component 520 is the continuous rotation detonation engine 400 embodiment of the fourth aspect previously described. The aircraft 500 embodiment is provided with the fuel supply runner 100 embodiment, and therefore has the technical effect of the fuel supply runner 100 embodiment, wherein the improvement in the uniformity of the combustible mixture may increase thrust and mach number, and wherein the improvement in the circumferential uniformity of the combustible mixture may increase flight stability. And the complexity that an auxiliary gas phase fuel system needs to be configured in the aircraft adopting the liquid phase fuel continuous rotation detonation engine in the prior art is overcome, and the technical effects of improving the working reliability and the volume energy density are achieved.
Claims (10)
1. A fuel supply flow passage, characterized by comprising: a liquid phase flow channel assembly and a gas phase flow channel assembly;
the liquid phase flow channel assembly comprises two or more liquid phase flow channel sub-pieces, the structures of all the liquid phase flow channel sub-pieces are the same, and each liquid phase flow channel sub-piece comprises a liquid phase main channel and two or more liquid phase branch channels;
each liquid trunk has one or more liquid trunk inlets;
the outer wall surface of each liquid phase branch channel is locally cylindrical, each liquid phase branch channel is provided with a liquid phase branch channel outlet, the flow cross-section area of each liquid phase branch channel outlet is smaller than that of each liquid phase branch channel, and the flow cross-section areas of all the liquid phase branch channel outlets are equal;
the gas phase runner component comprises a gas phase main channel and two or more gas phase branch channels, and the gas phase main channel is provided with one or more gas phase main channel inlets;
each gas phase branch channel is provided with a gas phase branch channel front section, a gas phase branch channel rear section and a gas phase branch channel outlet;
each gas-phase branch passage rear section is a cylindrical hole, the axes of all the gas-phase branch passage rear section cylindrical holes are intersected at one point, and all the gas-phase branch passage rear section cylindrical holes are uniformly distributed in the circumferential direction;
the total number of the liquid phase branch passages is the same as that of the gas phase branch passages and corresponds to the gas phase branch passages one by one, the total number of the liquid phase branch passage outlets is the same as that of the gas phase branch passage outlets and corresponds to one, and the total number of the liquid phase branch passage outlets is greater than or equal to 12;
the diameter of the local cylindrical outer wall surface of each liquid phase branch channel is smaller than the diameter of the corresponding rear-section cylindrical hole of the gas phase branch channel, the local cylindrical outer wall surface of each liquid phase branch channel partially extends into the corresponding rear-section cylindrical hole of the gas phase branch channel, and the axis of the local cylindrical outer wall surface of each liquid phase branch channel and the axis of the corresponding rear-section cylindrical hole of the gas phase branch channel form a coaxial relationship.
2. The fuel supply flow passage according to claim 1, characterized in that: the liquid phase main road is characterized in that the shape of the central line of the liquid phase main road is circular arc, the circular arc radiuses of the central lines of all the liquid phase main roads are equal, the sum of the circular arcs of the central lines of all the liquid phase main roads is less than or equal to 2 pi, all the liquid phase main roads are uniformly distributed in the circumferential direction, the flow cross section of each liquid phase main road is circular, and the flow cross section area of each liquid phase main road is less than or equal to 4 square millimeters.
3. The fuel supply flow passage according to claim 1, characterized in that: the flow cross section of each liquid phase branch channel is circular, the flow cross section area of each liquid phase branch channel is less than or equal to 2 square millimeters, the flow cross section area of each liquid phase branch channel outlet is less than or equal to 0.2 square millimeters, and the flow cross section shape of each liquid phase branch channel outlet is circular.
4. The fuel supply flow passage according to claim 1, characterized in that: the shape of the flow cross section of the front section of each gas phase branch channel is circular.
5. The fuel supply flow passage according to claim 1, characterized in that: the total number of the liquid phase branch outlets is greater than or equal to 30.
6. The fuel supply flow passage according to claim 1, characterized in that: the difference between the diameter of the local cylindrical outer wall surface of each liquid phase branch channel and the diameter of the corresponding cylindrical hole at the rear section of the gas phase branch channel is less than or equal to 4mm, the geometric center point of the outlet of each corresponding liquid phase branch channel and the geometric center point of the outlet of the gas phase branch channel form a coincidence relation, and the whole set of liquid phase flow channel assembly has the structural strength and high hydraulic tightness, and the internal hydraulic pressure of the whole set of liquid phase flow channel assembly is greater than or equal to 30 MPa.
7. A fuel injection apparatus characterized in that: a fuel supply flow passage of claim 1 and a fuel flow opening/closing actuator; the number of the fuel flow on-off executing components is the same as the total number of the inlets of the liquid-phase trunk, the fuel flow on-off executing components correspond to the inlets of the liquid-phase trunk one by one, and each corresponding fuel flow on-off executing component and each corresponding inlet of the liquid-phase trunk are in high-hydraulic sealing fit with each other.
8. A fuel supply system includes a fuel storage section, a fuel pressurizing section, a fuel injection section; the fuel storage component and the fuel pressurizing component are connected through a pipeline, and the fuel pressurizing component and the fuel injection component are connected through a pipeline; the method is characterized in that: the fuel injection component is defined by the fuel injection device of claim 7.
9. A continuous rotary detonation engine comprising a fuel supply component, a combustion chamber component, a detonation component; the fuel supply component and the combustion chamber component are connected by a pipeline, and the detonation component extends into the combustion chamber component through a hole on the outer wall surface of the shell of the combustion chamber component; the method is characterized in that: the fuel supply component defines the fuel supply system of claim 8, and the fuel supply flow passage is connected to the outer wall surface of the housing of the combustor component by a connector for communication, fastening and high pressure sealing.
10. An aircraft comprising an engine component, a control component, a load component; the engine component and the control component are connected through a communication data line, the load component comprises an aircraft shell and a filler, and the filler, the control component and the engine component are sequentially arranged at the upper, middle and lower positions in the aircraft shell; the method is characterized in that: the engine component is defined as a continuous rotary detonation engine as claimed in claim 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210856744.8A CN115075953A (en) | 2022-07-20 | 2022-07-20 | Fuel supply flow passage, injection device, supply system, engine, and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210856744.8A CN115075953A (en) | 2022-07-20 | 2022-07-20 | Fuel supply flow passage, injection device, supply system, engine, and aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115075953A true CN115075953A (en) | 2022-09-20 |
Family
ID=83259097
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210856744.8A Pending CN115075953A (en) | 2022-07-20 | 2022-07-20 | Fuel supply flow passage, injection device, supply system, engine, and aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115075953A (en) |
-
2022
- 2022-07-20 CN CN202210856744.8A patent/CN115075953A/en active Pending
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN101354141B (en) | Fuel nozzle for gas turbine unit and manufacturing method thereof | |
| CN115628449B (en) | Gas-liquid coaxial centrifugal nozzle in assembly structure | |
| CN101737200A (en) | Modularized heat-capacity type thrust chamber | |
| CN113154448B (en) | Device for fuel injection and flame stabilization of supersonic combustion chamber of ramjet engine | |
| US10054314B2 (en) | Slotted injector for axial fuel staging | |
| CN1065589C (en) | Fuel injection valve for internal combustion engines | |
| CN111779577B (en) | Afterburner ignition system | |
| CN116537953A (en) | Turbine afterburner matching system of small turbojet engine booster afterburner | |
| CN113969849A (en) | Single-nozzle rocket engine with modular design | |
| CN109505711B (en) | Gas-gas small rocket device for generating high-temperature supersonic gas | |
| CN115075953A (en) | Fuel supply flow passage, injection device, supply system, engine, and aircraft | |
| CN107676195B (en) | A kind of modularization rocket engine propellant biasing spray panel of cover board connection | |
| CN111502860B (en) | Pressure swirl injector with modular design | |
| CN110700963B (en) | Compact layout type solid rocket gas scramjet engine based on axial symmetry | |
| WO2024093078A1 (en) | Variable thrust pintle type injector | |
| CN109695504B (en) | circumferential oil-supplementing cracking device | |
| CN115014778B (en) | Large-scale high-enthalpy wind tunnel inflow simulated combustion device | |
| WO2023200479A3 (en) | Multitube pilot injection into trapped vortices in a gas turbine engine | |
| CN110886657A (en) | Plasma ignition system of air-breathing engine | |
| WO1995014164A1 (en) | Carburettor | |
| CN115075952A (en) | Fuel supply flow passage, injection device, supply system, engine, and aircraft | |
| CN115614184A (en) | Small-sized steam generator | |
| CN101644210A (en) | Combined nozzle fuel gas fluid control valve | |
| CN113819465A (en) | Flow-adjustable gas oxygen and methane rich combustion gas generation device and method | |
| CN108757222B (en) | Three-component integrated nozzle assembly |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |