CN204344285U - A kind of aircraft engine oil lubrication intensification safeguards system - Google Patents
A kind of aircraft engine oil lubrication intensification safeguards system Download PDFInfo
- Publication number
- CN204344285U CN204344285U CN201420657457.5U CN201420657457U CN204344285U CN 204344285 U CN204344285 U CN 204344285U CN 201420657457 U CN201420657457 U CN 201420657457U CN 204344285 U CN204344285 U CN 204344285U
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- pipe
- air
- intensification
- oil lubrication
- jet nozzle
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- Lubrication Of Internal Combustion Engines (AREA)
Abstract
The utility model discloses a kind of aircraft engine oil lubrication intensification safeguards system, its formation comprises, the air entraining pipe be communicated with air starter high temperature air leading pipe, control air entraining pipe and lead to the solenoid valve closed, jet nozzle, be designed with and be no less than two heating pipes adding hot leg pipe and be arranged on the switch controlling solenoid valve in cockpit, described solenoid valve is arranged between two sections of bleed air line, described jet nozzle is connected with air entraining pipe outlet end and heating pipe entrance point respectively, inlet of cold air is designed with around jet nozzle, cool air enters heating pipe by inlet of cold air under jet effect effect, hot air is mixed to form with jet high temperature air, sprayed by heating branch outlet and engine surface different parts is heated, make sliding oil heating in engine system to set point of temperature.Aeroengine is equipped with oil lubrication intensification safeguards system of the present utility model, can in ambient temperature-55 DEG C of situations normal starting, breach aeroengine low temperature environment start bottom line.
Description
Technical field
The utility model relates to aeroengine cold-starting safeguards technique, particularly a kind of aircraft engine oil lubrication intensification safeguards system.
Background technique
In order to ensure aeroengine security of operation and working life, all the needing everywhere of motor is lubricated, and aeroengine is a kind of dynamic power machine very high to oil lubrication performance requirement.Although the lubricant oil that aeroengine the uses lubricant oil that normally performance is best, but the feature had equally along with ambient temperature reduction greasy property reduces, certain requirement is had to Environmental Conditions temperature, usually when ambient temperature is lower than-30 DEG C, the greasy property of lubricant oil will reduce greatly, lose greasy property, aeroengine cannot normally start, and aircraft can not take off.Therefore, in the ordinary course of things, when ground ambient temperature is lower than-30 DEG C, aircraft does not take off.In a special case, if aircraft must take off, usually take the environment around by aircraft to be warming up to more than-30 DEG C, make lubricant oil return to normal greasy property, restart motor, aircraft just can take off.
Summary of the invention
For the state of the art that aeroengine cannot normally start below-30 DEG C, the purpose of this utility model aims to provide a kind of aircraft engine oil lubrication intensification safeguards system, normally starts under ensureing the ground environment temperature of aeroengine below-30 DEG C.
Basic thought of the present utility model is, high temperature air drawn by the bleed conduit of air starter, the introducing oil lubrication intensification safeguards system of high temperature air is controlled by solenoid valve, in system, utilize jet nozzle to be sprayed from inlet tube high speed by high temperature air, the jet high temperature air entered in heating pipe mixes with the cold sky that jet effect sucks, engine nacelle different parts is ejected into by the hot leg pipe that adds of heating pipe, make sliding oil heating in engine system to set point of temperature, to ensure that aeroengine starts under extremely cold low temperature environment.
Technical problem to be solved in the utility model, the aircraft engine oil lubrication intensification safeguards system by following technical proposals realizes.
The aircraft engine oil lubrication intensification safeguards system that the utility model provides, its formation comprises, the air entraining pipe that engine nacelle outer wall is communicated with air starter high temperature air leading pipe is set, control air entraining pipe and lead to the solenoid valve closed, jet nozzle, be designed with and be no less than two heating pipes adding hot leg pipe and be arranged on the switch controlling solenoid valve in cockpit, described solenoid valve is arranged between two sections of bleed air line, described jet nozzle is connected with air entraining pipe outlet end and heating pipe entrance point respectively, inlet of cold air is designed with around jet nozzle, high temperature air in air entraining pipe forms jet through jet nozzle ejection, cool air enters heating pipe by inlet of cold air under jet effect effect, hot air is mixed to form with jet high temperature air, sprayed by heating branch outlet and engine surface different parts is heated, sliding oil heating is made to arrive the temperature of regulation.
In technique scheme of the present utility model, described heating pipe is designed with the import termination containing connecing jet nozzle, described suction port termination is designed with the lip containing connecing jet nozzle, lip is designed with and is no less than three uniform boss, boss is designed with tapped hole air entraining pipe, jet nozzle and heating pipe are fixed together by bolt, the breach between boss is inlet of cold air.
In technique scheme of the present utility model, described heating pipe pays the utmost attention to the heating pipe being designed to the fork configuration being provided with two arms, what namely connect two parallel-connection structures after an intake header adds hot leg pipe, and the hot air sprayed by arm is positioned at engine nacelle shell wall side and the driving engine part be positioned on engine nacelle shell wall side for heating.
In technique scheme of the present utility model, described fork-shaped heating pipe inducer, the leading portion of inducer can be considered to be designed to prismatic pipe; Further, apart from import 2.5 ~ 3.5 times of caliber places, can consider design one expand-restrain structure, the high temperature air entered from introduction tube jet is fully mixed with the cool air entered.Again further, the heating branch outlet of described fork-shaped heating pipe, is preferably designed to expanding spout, to reduce the speed of hot air ejection.
In technique scheme of the present utility model, described two sections of air entraining pipes are preferably formed by metal material rigid pipe and programming structure pipe.Air entraining pipe is designed to be made up of metal material rigid pipe and programming structure pipe, the installation question under the fixing situation of air entraining pipe two ends can be solved, wherein the effect of programming structure pipe, applicable cast can be regulated, convenient installation.Because introduced gas is high-temperature gas, described programming structure pipe preferentially adopts silicone rubber and glass fibre to mix the structural tube be compiled into.
In technique scheme of the present utility model, described jet nozzle preferentially adopts the jet nozzle of single convergence structure.
The aircraft engine oil lubrication intensification safeguards system that the utility model provides, it is the high temperature air utilizing aircraft auxiliary power plant to provide for engine air starter motor, high temperature air drawn by the high temperature air bleed conduit of air starter, by being arranged on the switch in cockpit, control high temperature air by solenoid valve and introduce oil lubrication intensification safeguards system, in system, utilize jet nozzle to be sprayed from high temperature inlet tube high speed by high temperature air, the hot air that jet high temperature air and cool air are mixed to form, engine nacelle different parts is ejected into by the hot leg pipe that adds of heating pipe, sliding oil heating is made to arrive the temperature of regulation, to ensure that aeroengine starts under extremely cold low temperature.Aeroengine is equipped with oil lubrication intensification safeguards system of the present utility model, can in ground environment temperature-55 DEG C of situations normal starting, and aircraft lubricating oil best at present can only ensure that aeroengine normally uses under the environment of subzero 40 °, breach the bottom line that aeroengine low temperature environment starts.
Accompanying drawing explanation
Accompanying drawing 1 is the schematic diagram that oil lubrication intensification safeguards system of the present utility model is assemblied in aeroengine, and thick line portion is scope of the present utility model.
Accompanying drawing 2 is structural representations of oil lubrication intensification safeguards system of the present utility model.
Accompanying drawing 3 is structure for amplifying schematic diagram of I part in accompanying drawing 2.
Accompanying drawing 4 is side-looking structural representations of accompanying drawing 3.
In above-mentioned accompanying drawing, the object of each shown by reference numeral mark is respectively: 1-metal material rigid pipe; 2-solenoid valve; 3-programming structure pipe; 4 heating pipes; 5-jet nozzle; 6-inlet of cold air; 7-import termination.
Embodiment
Provide embodiment of the present utility model below in conjunction with accompanying drawing, and by embodiment, the utility model is further described specifically.What be necessary to herein means out is; embodiment is only for the utility model is described in further detail; the restriction to the utility model protection domain can not be interpreted as; the person skilled in the art in this field can make some nonessential improvement according to above-mentioned content of the present utility model and adjustment is implemented, but such enforcement should still belong to protection domain of the present utility model.
Embodiment 1
The implementation case aircraft engine oil lubrication intensification safeguards system, its structure is as accompanying drawing 2, shown in accompanying drawing 3 and accompanying drawing 4, form and comprise the air entraining pipe be communicated with air starter high temperature air leading pipe, control air entraining pipe and lead to the solenoid valve 2 closed, jet nozzle, be designed with two add the fork-shaped heating pipe 4 of hot leg pipe and be arranged on the switch controlling solenoid valve in cockpit, described solenoid valve is arranged between two sections of bleed air line, described jet nozzle is the jet nozzle of single convergence structure, be connected with air entraining pipe outlet end and heating pipe entrance point respectively with bolt by adpting flange.Described two sections of air entraining pipes are formed by metal material rigid pipe 1 and programming structure pipe 3, and described metal material rigid pipe is Stainless Steel Tube, and described programming structure pipe 3 is mix by silicone rubber and glass fibre the structural tube be compiled into.Described heating pipe is designed with the import termination 7 be connected with jet nozzle, described suction port termination is designed with the lip containing connecing jet nozzle, lip is designed with three uniform boss, boss is designed with tapped hole air entraining pipe, jet nozzle and heating pipe are fixed together by bolt, the breach between boss is inlet of cold air 6.The leading portion of described fork-shaped heating pipe inducer is prismatic pipe, an expansion-convergence structure is being designed with apart from import 2.5 ~ 3.5 times of caliber places, the cool air of high temperature air and the suction entered from introduction tube jet is fully mixed, and the heating branch outlet of described fork-shaped heating pipe is expanding spout.
Claims (10)
1. an aircraft engine oil lubrication intensification safeguards system, it is characterized in that, comprise the air entraining pipe being arranged on aeroengine nacelle outer wall and being communicated with air starter high temperature air leading pipe, control air entraining pipe and lead to the solenoid valve (2) closed, jet nozzle (5), be designed with and be no less than two heating pipes (4) adding hot leg pipe and be arranged on the switch controlling solenoid valve in cockpit, described solenoid valve is arranged between two sections of air entraining pipes, described jet nozzle is connected with air entraining pipe outlet end and heating pipe entrance point respectively, inlet of cold air (6) is designed with around jet nozzle, high temperature air in air entraining pipe forms jet through jet nozzle ejection, cool air enters into heating pipe by inlet of cold air under jet effect effect, hot air is mixed to form with jet high temperature air, sprayed by heating branch outlet and engine surface different parts is heated, sliding oil heating is made to arrive the temperature of regulation.
2. aircraft engine oil lubrication intensification safeguards system according to claim 1, it is characterized in that, described heating pipe is designed with the import termination (7) containing connecing jet nozzle, described suction port termination is designed with the lip containing connecing jet nozzle, lip is designed with and is no less than three uniform boss, boss is designed with tapped hole air entraining pipe, jet nozzle and heating pipe are fixed together by bolt, the breach between boss is inlet of cold air.
3. boat aircraft engine oil lubrication intensification safeguards system according to claim 1 and 2, it is characterized in that, described heating pipe is be provided with the heating pipe that two add the fork configuration of hot leg pipe.
4. aircraft engine oil lubrication intensification safeguards system according to claim 3, it is characterized in that, described fork-shaped heating pipe inducer is uniform section pipe.
5. aircraft engine oil lubrication intensification safeguards system according to claim 4, it is characterized in that, described fork-shaped heating pipe is being designed with expansion-convergence structure apart from import 2.5 ~ 3.5 times of caliber places.
6. aircraft engine oil lubrication intensification safeguards system according to claim 5, it is characterized in that, the heating branch outlet of described fork-shaped heating pipe is expanding spout.
7. aircraft engine oil lubrication intensification safeguards system according to claim 1 and 2, it is characterized in that, described two sections of air entraining pipes are formed by metal material rigid pipe (1) and programming structure pipe (3).
8. aircraft engine oil lubrication intensification safeguards system according to claim 6, it is characterized in that, described two sections of air entraining pipes are formed by metal material rigid pipe (1) and programming structure pipe (3).
9. aircraft engine oil lubrication intensification safeguards system according to claim 8, it is characterized in that, described programming structure pipe is mix by silicone rubber and glass fibre the structural tube be compiled into.
10. aircraft engine oil lubrication intensification safeguards system according to claim 1 and 2, it is characterized in that, described jet nozzle is the jet nozzle of single convergence structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420657457.5U CN204344285U (en) | 2014-11-05 | 2014-11-05 | A kind of aircraft engine oil lubrication intensification safeguards system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420657457.5U CN204344285U (en) | 2014-11-05 | 2014-11-05 | A kind of aircraft engine oil lubrication intensification safeguards system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204344285U true CN204344285U (en) | 2015-05-20 |
Family
ID=53227559
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420657457.5U Withdrawn - After Issue CN204344285U (en) | 2014-11-05 | 2014-11-05 | A kind of aircraft engine oil lubrication intensification safeguards system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204344285U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104373218A (en) * | 2014-11-05 | 2015-02-25 | 成都发动机（集团）有限公司 | Lubricating oil lubricating and heating support system for aircraft engine |
| CN109312631A (en) * | 2016-06-13 | 2019-02-05 | 通用电气公司 | For reducing the system and method for the fluid viscosity in gas-turbine unit |
-
2014
- 2014-11-05 CN CN201420657457.5U patent/CN204344285U/en not_active Withdrawn - After Issue
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104373218A (en) * | 2014-11-05 | 2015-02-25 | 成都发动机（集团）有限公司 | Lubricating oil lubricating and heating support system for aircraft engine |
| CN109312631A (en) * | 2016-06-13 | 2019-02-05 | 通用电气公司 | For reducing the system and method for the fluid viscosity in gas-turbine unit |
| CN109312631B (en) * | 2016-06-13 | 2021-08-17 | 通用电气公司 | System and method for reducing fluid viscosity in a gas turbine engine |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20150520 Effective date of abandoning: 20160824 |
|
| C25 | Abandonment of patent right or utility model to avoid double patenting |