CN216894697U - Premixed fuel system in crankcase of high-speed two-stroke aviation diesel engine - Google Patents
Premixed fuel system in crankcase of high-speed two-stroke aviation diesel engine Download PDFInfo
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- CN216894697U CN216894697U CN202220355795.8U CN202220355795U CN216894697U CN 216894697 U CN216894697 U CN 216894697U CN 202220355795 U CN202220355795 U CN 202220355795U CN 216894697 U CN216894697 U CN 216894697U
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- engine
- crankcase
- common rail
- oil pump
- diesel engine
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T10/00—Road transport of goods or passengers
- Y02T10/10—Internal combustion engine [ICE] based vehicles
- Y02T10/30—Use of alternative fuels, e.g. biofuels
Abstract
The utility model discloses a premixed fuel system in a crankcase of a high-speed two-stroke aviation diesel engine, which comprises a high-pressure oil pump assembly, a common rail pipe assembly connected with the high-pressure oil pump assembly, an in-cylinder direct injection fuel injector connected with the common rail pipe assembly, and an electric control lubrication fuel injector connected with the common rail pipe assembly and used for injecting atomized fuel oil for lubricating a transmission part into the crankcase. The premixed fuel system in the crankcase of the high-speed two-stroke aviation diesel engine can simultaneously meet the fuel injection requirement of a direct injection engine in the cylinder and the lubrication requirement of a transmission system of the engine, so that the engine does not need to be additionally provided with a lubrication system, the purpose of reducing the weight of the whole engine is achieved, and the weight and the complexity of the engine are reduced.
Description
Technical Field
The utility model belongs to the technical field of engines, and particularly relates to a premixed fuel system in a crankcase of a high-speed two-stroke aviation diesel engine.
Background
With the development of miniaturization of the current aircraft, the requirements for miniaturization and light weight of the engine are higher and higher. The existing aircraft engine needs to be provided with an independent lubricating oil system, so that the weight and the complexity of the engine are increased, the miniaturization of the engine is not facilitated, and the power-to-weight ratio of the engine is influenced.
SUMMERY OF THE UTILITY MODEL
The present invention is directed to solving at least one of the problems of the prior art. Therefore, the utility model provides a premixed fuel system in a crankcase of a high-speed two-stroke aviation diesel engine, aiming at reducing the weight and complexity of the engine.
In order to achieve the purpose, the utility model adopts the technical scheme that: premixed fuel system in high-speed two-stroke aviation diesel engine crankcase, including high-pressure oil pump subassembly, the common rail pipe assembly who is connected with the high-pressure oil pump subassembly, with the direct fuel injector of the in-cylinder that the common rail pipe assembly is connected and with the common rail pipe assembly is connected and is used for spouting the automatically controlled lubrication fuel injector that is used for lubricated transmission part's atomizing fuel in the crankcase.
The number of the direct injection oil injectors in the cylinder is two.
The high-pressure oil pump assembly is a plunger type high-pressure oil pump.
The premixed fuel system in the crankcase of the high-speed two-stroke aviation diesel engine can simultaneously meet the fuel injection requirement of a direct injection engine in a cylinder and the lubrication requirement of an engine transmission system, so that the engine does not need an additional lubrication system, the aim of reducing the weight of the whole engine is fulfilled, and the weight and the complexity of the engine are reduced.
Drawings
The description includes the following figures, the contents shown are respectively:
FIG. 1 is a schematic illustration of the pre-mixed fuel system within the crankcase of the high speed two-stroke aero-diesel engine of the present invention;
FIG. 2 is a position of an in-cylinder direct injection fuel injector and a lubrication fuel injector mounted on an engine;
FIG. 3 is a high pressure oil pump assembly;
FIG. 4 is a common rail tube assembly;
FIG. 5 is an in-cylinder direct injection injector assembly/electronically controlled lubrication injector assembly;
labeled as: 1. a high pressure oil pump assembly; 2. a common rail pipe assembly; 3. an in-cylinder direct injection fuel injector; 4. an electrically controlled lubrication fuel injector; 5. an oil pipe assembly; 6. a crankshaft bearing; 7. a piston connecting rod; 8. a crankcase.
Detailed Description
The following detailed description of the embodiments of the present invention will be given with reference to the accompanying drawings for a purpose of helping those skilled in the art to more fully, accurately and deeply understand the concept and technical solution of the present invention and to facilitate its implementation.
As shown in fig. 1 to 5, the utility model provides a premixed fuel system in a crankcase of a high-speed two-stroke aviation diesel engine, which comprises a high-pressure oil pump assembly 1, a common rail pipe assembly 2 connected with the high-pressure oil pump assembly 1, an in-cylinder direct injection injector 3 connected with the common rail pipe assembly 2, and an electronic control lubrication injector 4 connected with the common rail pipe assembly 2 and used for injecting atomized fuel for lubricating transmission parts into a crankcase 8.
Specifically, as shown in fig. 1 and 2, an oil outlet of the high-pressure oil pump assembly 1 is connected with the common rail pipe assembly 2 through an oil pipe, an oil outlet of the common rail pipe assembly 2 is connected with the in-cylinder direct injection injector 3 through an oil pipe assembly 5, the in-cylinder direct injection injector 3 is mounted on the engine body, the in-cylinder direct injection injectors 3 are arranged in two numbers, and the high-pressure oil pump assembly 1, the common rail pipe assembly 2, the oil pipe assembly 5 and the in-cylinder direct injection injector 3 form a high-pressure common rail fuel system to provide sufficient fuel supply for engine combustion. The electric control lubrication oil injector 4 is connected with an oil outlet of the common rail pipe component 2 through an oil pipe, the high-pressure oil pump component 1, the common rail pipe component 2 and the electric control lubrication oil injector 4 form an engine lubrication system, a proper amount of atomized fuel oil is injected into a crankcase 8 through controlling the electric control lubrication oil injector 4 to lubricate transmission parts such as a crankshaft bearing 6, a piston connecting rod 7 and the like, and meanwhile, part of fuel oil which is not attached to the transmission parts enters a combustion chamber through an air inlet to participate in combustion so as to prevent the fuel oil from accumulating in the crankcase 8.
As shown in fig. 1 and 2, the high-pressure oil pump assembly 1 is a plunger type high-pressure oil pump, a high-pressure interface of the high-pressure oil pump is communicated with a high-pressure rail pipe through an oil pipe assembly 5, and the high-pressure oil pump can provide 100-200 bar high-pressure fuel oil for a fuel system.
In order to further reduce the complexity of the system, the electric control lubrication oil injector 4 and the in-cylinder direct injection oil injector 3 are oil injectors with the same structure.
The utility model is described above with reference to the accompanying drawings. It is to be understood that the specific implementations of the utility model are not limited in this respect. Various insubstantial improvements are made by adopting the method conception and the technical scheme of the utility model; the present invention is not limited to the above embodiments, and can be modified in various ways.
Claims (3)
1. Premixed fuel system in high-speed two-stroke aviation diesel engine crankcase, including high-pressure oil pump subassembly, with the common rail pipe subassembly that high-pressure oil pump subassembly is connected and with the direct sprayer of spouting of the jar that common rail pipe subassembly is connected, its characterized in that: the electric control lubrication oil injector is connected with the common rail pipe assembly and used for injecting atomized fuel oil for lubricating a transmission part into a crankcase.
2. The high speed two-stroke aero diesel engine crankcase pre-mixed fuel system of claim 1 wherein: the number of the direct injection oil injectors in the cylinder is two.
3. The high speed two-stroke aero diesel engine crankcase pre-mixed fuel system according to claim 1 or 2, wherein: the high-pressure oil pump assembly is a plunger type high-pressure oil pump.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202220355795.8U CN216894697U (en) | 2022-02-22 | 2022-02-22 | Premixed fuel system in crankcase of high-speed two-stroke aviation diesel engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202220355795.8U CN216894697U (en) | 2022-02-22 | 2022-02-22 | Premixed fuel system in crankcase of high-speed two-stroke aviation diesel engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN216894697U true CN216894697U (en) | 2022-07-05 |
Family
ID=82185029
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202220355795.8U Active CN216894697U (en) | 2022-02-22 | 2022-02-22 | Premixed fuel system in crankcase of high-speed two-stroke aviation diesel engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN216894697U (en) |
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2022
- 2022-02-22 CN CN202220355795.8U patent/CN216894697U/en active Active
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