CN2142503Y - High-speed boosting jet engine - Google Patents
High-speed boosting jet engine Download PDFInfo
- Publication number
- CN2142503Y CN2142503Y CN 92230113 CN92230113U CN2142503Y CN 2142503 Y CN2142503 Y CN 2142503Y CN 92230113 CN92230113 CN 92230113 CN 92230113 U CN92230113 U CN 92230113U CN 2142503 Y CN2142503 Y CN 2142503Y
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- Prior art keywords
- oil
- pressure
- axial flow
- main shaft
- cylinder block
- 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.)
- Expired - Lifetime
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- 239000007788 liquid Substances 0.000 claims abstract description 6
- 239000003921 oil Substances 0.000 claims description 56
- 238000010304 firing Methods 0.000 claims description 23
- 239000000446 fuel Substances 0.000 claims description 23
- 238000001816 cooling Methods 0.000 claims description 6
- 230000000694 effects Effects 0.000 claims description 6
- 238000002347 injection Methods 0.000 claims description 6
- 239000007924 injection Substances 0.000 claims description 6
- 239000010687 lubricating oil Substances 0.000 claims description 5
- 238000002156 mixing Methods 0.000 claims description 4
- 238000002485 combustion reaction Methods 0.000 abstract description 6
- 239000007789 gas Substances 0.000 description 7
- 238000001704 evaporation Methods 0.000 description 3
- 239000010720 hydraulic oil Substances 0.000 description 3
- 238000001914 filtration Methods 0.000 description 2
- 238000007689 inspection Methods 0.000 description 2
- 239000000314 lubricant Substances 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 239000000203 mixture Substances 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 1
- 235000019504 cigarettes Nutrition 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000003912 environmental pollution Methods 0.000 description 1
- 230000008020 evaporation Effects 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 238000005286 illumination Methods 0.000 description 1
- 239000010721 machine oil Substances 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 238000010025 steaming Methods 0.000 description 1
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- Engine Equipment That Uses Special Cycles (AREA)
Abstract
The utility model provides a high-speed pressure boost jet engine, it includes parts such as main shaft, DC generator, cylinder block, axial compressor rim plate rotor bulldozer, oil pan, axial-flow type flywheel, air cleaner, combustion chamber. The engine is provided with three cylinder bodies and three axial flow wheel disc rotor pushers, and high-pressure air, high-pressure liquid oil and high-pressure mixed gas flow are respectively sprayed to the wheel edges of the axial flow wheel disc rotor pushers to push the engine to rotate at a high speed, so that the engine has the characteristics of high rotating speed, stable operation, high power, less oil consumption, simple structure and low cost. It is suitable for use as prime mover in airplane, ship, train, automobile and other motor vehicles.
Description
The utility model relates to a kind of high-speed boosting jet-type engine, is applicable to the usefulness of the power engine that aircraft, steamer, train, automobile, motorcycle and farm machinery etc. are general.
Existing motor has Reciprocating engine, turbojet engine and rotary engine etc., their pressure spot is all in the central position, has no precedent pressure spot on the rotor wheel limit.
Disclose a kind of motor in NL7415906, this motor has three cylinder rotor ， And by the star fixed arrangement that the pistons reciprocating that motion is controlled by the roller in the engine cam groove is housed.Air by the piston that moves upward be drawn into Xia the piston Mian ， And by means of bypass channel top air compression.Piston is equipped by the taper overhang of working together with the firing chamber, and the pressure on firing chamber internal surface between the phase of expansion produces a couple on gyrator, so, to rotate with regard to central shaft around the chamber, the cooling means of exhaust and air just provides.Its major defect is that piston is reciprocatory motion, because the effect of inertia of mechanical motion so vibration and power loss are all very big, causes engine running not steady, fuel consumption is big, and output power is few, and rotating speed is low.
In turbojet engine, it must move under very high rotating speed in order to obtain higher pressure ratio, therefore to finish by the gas compressor that multistage rotor blade and stator vane are formed, thus its complex structure, difficult manufacturing, cost height.Because it does not have airtight air chamber, and pressure ratio sharply reduces when low speed rotation, and output torque reduces sharply, and makes rear axle bear temperatures involved, cause working life short simultaneously.
In rotary engine, rotor shaft decentraction, the planetary mechanism that main machine frame is made up of external gear and eccentric shaft in a pair of phase place, the theory shaped wire of rotor are the interior envelope of cylinder profile family, the geometrical principle complexity, manufacture difficulty is big, and being shaped as of firing chamber is flat partially box-like, so the area of firing chamber is big, combustion efficiency is low, the pressurized seal difficulty is prone to cylinder body shake line very much, and engine performance is significantly descended.
The purpose of this utility model is original engine pressure point is changed into pressure spot on the wheel limit in the central position, overcome the effect of inertia of mechanical motion, thereby provide a kind of output power big, the rotating speed height, running steadily, the high-speed boosting jet-type engine of energy saving is widely used in the usefulness that aircraft, steamer, train, automobile, motorcycle, farm machinery etc. provide power.
The purpose of this utility model reaches by following approach:
The utility model comprises parts such as main shaft, high-pressure turbine fan, DC generator, cylinder block, axial flow disk rotors pusher, oil sump, axial flow flywheel, air-strainer, oil filter and firing chamber.With screw cylinder block that the structure of San And row is identical and its head and the tail and between set four cylinder caps fastening; Be provided with a main shaft in cylinder block and cylinder cap center, it is fixed on the central position of two cylinder caps of head and the tail by the bearing activity; Front end at main shaft is fixed with the high-pressure turbine fan with retaining screw, drives its rotation by main shaft, reaches the inside and outside purpose of cooled engine; Between preceding step bearing on the main shaft and high-pressure turbine fan, be provided with DC generator,, be used for the usefulness of ignition start and illumination by its rotary electrification of main shaft band; In three cylinder block, be equipped with and be fixed on main shaft Shang And and the identical axial flow disk rotors pusher of structure, diaphragm seal with constant slope is installed thereon, when engine revolution, be subjected to centrifugal action, make and produce slight friction between diaphragm seal and cylinder wall, sealability is strengthened, thereby the minimizing resistance improves rotating speed, increases power; Between cylinder block and cylinder cap, be provided with the cooling air inlet duct that is interconnected; In the cylinder block of front end, be provided with and be fixed on the air-strainer that one-level compressed pneumatic pump that main shaft Shang And links to each other with the secondary high-pressure pump communicates, high pressure air after the filtering is taken turns on the limit through the axial flow disk rotors pusher that the secondary high-pressure pump is ejected into the high-pressure air sparger in the front end cylinder block again by the one-level compressed pneumatic pump, make the high engine speeds rotation, simultaneously also high-pressure air is led to the firing chamber by the high-pressure jet pipe, be provided with coupled logical oil filter above the oil lubricating oil pump that is located on the main shaft, taking out the lubricant oil that comes by the oil lubricating oil pump, to lead to each lubricant housings by lubricated main oil pipe after filtering used; The axial flow disk rotors pusher that is provided with in the middle cylinders body is hydraulic oil to be ejected on its wheel limit through the high-pressure liquid jet pipe from the secondary high pressure oil pump of hydraulic oil through being fixed on the main shaft that the fuel sucking pipe suction comes by the one-level hydraulic-pressure pump that is installed on the main shaft again, make the high engine speeds rotation, at the bottom of this axial flow disk rotors pusher, be provided with an oil drainage hole, lead to oil sump, simultaneously, on the main shaft set co-fuel pump with fuel sucking pipe inhale the fuel that comes by fuel combination high-pressure injection pipe inspection to the firing chamber, be provided with the direct current igniter at the firing chamber correct position, this firing chamber is an evaporation-combustion chamber, the fueling injection equipment of firing chamber adopts evaporating pipe, it is evaporated a Guan Jiare steaming And formation inflammable mixture with high-pressure jet pipe and the next gas mixture that high-pressure air and fuel mixed of fuel combination high-pressure injection pipe inspection, for the burning of main zone of combustion, evaporating pipe is installed in the main burning region, heated by high-temperature fuel gas, owing to enter the fuel oil fully evaporation of firing chamber, oil gas mixes fully, therefore exhaust is fuming few, the combustion efficiency height, the oil gas that is produced by the firing chamber enters axial flow disk rotors pusher wheel limit set in the rear cylinder body, makes the high engine speeds rotation; Be fixed with axial flow flywheel and Flywheel machine shell at the main shaft end, the axial flow flywheel mainly is to cooperate pressurized air that the mixing exhaust pipe discharged front air cylinder body and rear cylinder body and mixed combustion smog and tail gas to discharge; Correct position is provided with the DC start motor above the axial flow flywheel; Be provided with shell in high-pressure turbine fan outside; Bottom in cylinder block is fixed with oil sump with fastening piece, and oil sump is divided into three, respectively is provided with an oil filling pipe, a fuel sucking pipe and an oil-draining locknut at correct position respectively, makes oiling, the oil suction of machine oil, fuel combination and hydraulic oil and the usefulness of draining the oil respectively.
Fig. 1 is a plan view of the present utility model, wherein:
The 1-retaining screw, 2-high-pressure turbine fan, the 3-shell, the 4-DC generator, the 5-bearing, the 6-cylinder cap, 7-axial flow disk rotors pusher, the 8-cylinder block, the 9-oil sump, the 10-oil filling pipe, the 11-screw, the 12-oil-draining locknut, the 13-fuel sucking pipe, 14-axial flow flywheel, 15-mixing exhaust pipe, the 16-main shaft, 17-one-level compressed pneumatic pump, 18-lubricates main oil pipe, the 19-air-strainer, 20-secondary high-pressure pump, 21-oil lubricating oil pump, the 22-oil filter, 23-high-pressure air sparger, 24-high-pressure jet pipe, 25-high-pressure liquid jet pipe, 26-cools off air inlet duct, 27-fuel combination high-pressure injection pipe, the 28-firing chamber, 29-direct current igniter, the 30-co-fuel pump, 31-secondary high pressure oil pump, 32-one-level hydraulic-pressure pump, 33-DC start motor, 34-Flywheel machine shell, the 35-oil drainage hole.
Fig. 2 is the left side view of Fig. 1.
Fig. 3 is the B-B sectional view of Fig. 1, wherein 36-diaphragm seal.
Fig. 4 is the C-C sectional view of Fig. 1.
Fig. 5 is the right side view of Fig. 1.
The utility model describes in detail below with reference to accompanying drawing embodiment:
The utility model embodiment comprises main shaft (16), high-pressure turbine fan (2), DC generator (4), cylinder block (8), axial flow disk rotors pusher (7), oil sump (9), axial flow flywheel (14), air-strainer (19), oil filter (22) and firing chamber parts such as (28).With screw (11) with the cylinder block (8) of San And row and its head and the tail and between set four cylinder caps (6) fastening; Be provided with a main shaft (16) in cylinder block (8) and cylinder cap (6) center, it is fixed on the central position of two cylinder caps of head and the tail (6) by bearing (5) activity; Front end at main shaft (16) is fixed with high-pressure turbine fan (2) with retaining screw (1), is provided with DC generator (4) between preceding step bearing (5) on the main shaft (16) and high-pressure turbine fan (2); In three cylinder block (8), be equipped with the axial flow disk rotors pusher (7) that is fixed on the main shaft (16); In the cylinder block (8) of front end, be provided with and be fixed on the main shaft (air-strainer (19) that the one-level compressed pneumatic pump (17) that 16) Shang And link to each other with secondary high-pressure pump (20) communicates, being provided with high-pressure air sparger (23) And between the wheel limit of the axial flow disk rotors pusher (7) in secondary high-pressure pump (20) and front end cylinder block (8) is provided with high-pressure jet pipe (24) and makes and communicate with each other between high-pressure air sparger (23) and set firing chamber (28), be provided with the oil filter (22) that is communicated with it in oil lubricating oil pump (21) top that is located on the main shaft (16), between oil filter (22) and each axial flow disk rotors pusher (7) wheel limit, be provided with lubricated main oil pipe (18); On cylinder block (8) inner main axis (16) of centre, be provided with co-fuel pump (30), secondary high pressure oil pump (31), one-level hydraulic-pressure pump (32) successively, co-fuel pump (30) is communicated with And with the oil header (13) of centre and is provided with injection pipe (27) between co-fuel pump (30) and firing chamber (28), is provided with high-pressure liquid jet pipe (25) between the wheel limit of the axial flow disk rotors pusher (7) in secondary high pressure oil pump (31) and middle cylinders body (8); One-level hydraulic-pressure pump (32) is communicated with the fuel sucking pipe (13) of secondary high pressure oil pump (31) and back respectively; Be interconnected at correct position between the axial flow disk rotors pusher (7) in firing chamber (28) and rear cylinder body (8); (14) ， And are provided with DC start motor (33) in the top of axial flow flywheel (14) to be fixed with the axial flow flywheel at main shaft (16) end; Bottom in cylinder block (8) is provided with oil sump.
Thickness be installed be 1.8 millimeters and become the diaphragm seals (36) of 36 degree gradients with vertical plane on said axial flow disk rotors pusher (7).
Between said cylinder block (8) and cylinder cap (6), be provided with the cooling air inlet duct (26) that is interconnected.
Bottom in the cylinder block (8) of said centre is provided with an oil drainage hole (35) that leads to oil sump (9).
The left side of (28) is provided with a direct current igniter (29) in the firing chamber.
The Flywheel machine shell is housed in said axial flow flywheel (14) outside, and (34) ， And are provided with mixing exhaust pipe (15) thereon, are provided with shell (3) in said high-pressure turbine fan (2) outside.
Said oil sump (9) is divided into three, respectively is provided with an oil filling pipe (10), a fuel sucking pipe (13) and an oil-draining locknut (12) respectively.
The utility model has following advantage compared to existing technology:
1, the utlity model has three cylinder block, three axial flow disk rotors pushers, promote axial flow disk rotors pusher High Rotation Speed by pressure-air, highly pressurised liquid oil and high-pressure gas stream respectively, because pressure spot is on the wheel limit, so simple in structure, cost is low, but smooth running energy savings 60% also;
2, the utility model is owing to be equipped with diaphragm seal at axial flow disk rotors pusher, so good sealing effect, and the engine rotation resistance is little, the rotating speed height, and power is big;
3, owing to the utlity model has the high-pressure turbine fan and the air intake cooling duct that communicates being arranged between cylinder cap, cylinder block, so engine cooling is effective;
4, can both fully burn gas and fuel in firing chamber of the present utility model, so cigarette is few, free from environmental pollution.
Claims (7)
1, a kind of high-speed boosting jet-type engine, include main shaft (16), high-pressure turbine fan (2), DC generator (4), cylinder block (8), axial flow disk rotors pusher (7), oil sump (9), axial flow flywheel (14), air-strainer (19), oil filter (22) and firing chamber parts such as (28), it is characterized in that it be with screw (11) cylinder block (8) that the structure of San And row is identical and its head and the tail and between set four cylinder caps (6) fastening; Be provided with a main shaft (16) in cylinder block (8) and cylinder cap (6) center, be fixed on the central position of two cylinder caps of head and the tail (6) by bearing (5) activity; Be fixed with high-pressure turbine fan (2) at main shaft (16) front end with retaining screw (1), between the preceding step bearing (5) of main shaft (16) and high-pressure turbine fan (2), be provided with DC generator (4); In three cylinder block (8), be equipped with and be fixed on main shaft (the axial flow disk rotors pusher (7) that 16) Shang And and structure are identical; In the cylinder block (8) of front end, be provided with and be fixed on the main shaft (air-strainer (19) that the one-level compressed pneumatic pump (17) that 16) Shang And link to each other with secondary high-pressure pump (20) communicates, be provided with high-pressure air sparger (23) And between the wheel limit of the axial flow disk rotors pusher (7) in secondary high-pressure pump (20) and front end cylinder block (8) and between high-pressure air sparger (23) and set firing chamber (28), be provided with high-pressure jet pipe (24), be provided with coupled logical oil filter (22) in oil lubricating oil pump (21) top that is located on the main shaft (16), between oil filter (22) and each axial flow disk rotors pusher (7) wheel limit, be provided with lubricated main oil pipe (18); In the cylinder block (8) of centre, be provided with co-fuel pump (30), secondary high pressure oil pump (31), one-level hydraulic-pressure pump (32) on the main shaft (16) successively, co-fuel pump (30) is communicated with And with the oil header (13) of centre and is provided with injection pipe (27) between co-fuel pump (30) and firing chamber (28), is provided with high-pressure liquid jet pipe (25) between the wheel limit of the axial flow disk rotors pusher in secondary high pressure oil pump (31) and middle cylinders body (8); One-level hydraulic-pressure pump (32) is communicated with the oil header (13) of secondary high pressure oil pump (31) and back respectively; Be interconnected at correct position between the axial flow disk rotors pusher (7) in firing chamber (28) and rear cylinder body (8); (14) ， And are provided with DC start motor (33) in the top of axial flow flywheel (14) to be fixed with the axial flow flywheel at main shaft (16) end; Bottom in cylinder block (8) is provided with oil sump.
2,, it is characterized in that being equipped with on the said axial flow disk rotors pusher (7) diaphragm seal (36) of constant slope by the described high-speed boosting jet-type engine of claim 1.
3, by the described high-speed boosting jet-type engine of claim 1, it is characterized in that being provided with between said cylinder block (8) and the cylinder cap (6) the cooling air inlet duct (26) that is interconnected.
4,, it is characterized in that said middle cylinders body (8) bottom is provided with an oil drainage hole (35) that leads to oil sump (9) by the described high-speed boosting jet-type engine of claim 1.
5, by the described high-speed boosting jet-type engine of claim 1, (34) ， And are provided with mixing exhaust pipe (15) thereon to it is characterized in that flywheel casing being housed said axial flow flywheel (14) outside.
6,, it is characterized in that said high-pressure turbine fan (2) outside is provided with shell (3) by the described high-speed boosting jet-type engine of claim 1.
7, by the described high-speed boosting jet-type engine of claim 1, it is characterized in that said oil sump (9) is divided into three, respectively be provided with an oil filling pipe (10), a fuel sucking pipe (13) and an oil-draining locknut (12) respectively.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 92230113 CN2142503Y (en) | 1992-08-04 | 1992-08-04 | High-speed boosting jet engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 92230113 CN2142503Y (en) | 1992-08-04 | 1992-08-04 | High-speed boosting jet engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN2142503Y true CN2142503Y (en) | 1993-09-22 |
Family
ID=33773314
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 92230113 Expired - Lifetime CN2142503Y (en) | 1992-08-04 | 1992-08-04 | High-speed boosting jet engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN2142503Y (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN100376764C (en) * | 2005-04-13 | 2008-03-26 | 蔡万义 | High-speed engine with hydraulic hybrid fuel jet devices and axial-flow flywheel vortex rotors |
| CN100378308C (en) * | 2006-07-07 | 2008-04-02 | 姜伟 | Impeller-pressurizing rotor-injection type steam turbine |
| CN100393983C (en) * | 2006-04-28 | 2008-06-11 | 蔡万义 | High-speed engine for hydraulic air-jet fly-wheel gas-turbine rotor |
| CN102003383A (en) * | 2009-08-27 | 2011-04-06 | 卡特彼勒公司 | Bearing arrangement for a pump |
-
1992
- 1992-08-04 CN CN 92230113 patent/CN2142503Y/en not_active Expired - Lifetime
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN100376764C (en) * | 2005-04-13 | 2008-03-26 | 蔡万义 | High-speed engine with hydraulic hybrid fuel jet devices and axial-flow flywheel vortex rotors |
| CN100393983C (en) * | 2006-04-28 | 2008-06-11 | 蔡万义 | High-speed engine for hydraulic air-jet fly-wheel gas-turbine rotor |
| CN100378308C (en) * | 2006-07-07 | 2008-04-02 | 姜伟 | Impeller-pressurizing rotor-injection type steam turbine |
| CN102003383A (en) * | 2009-08-27 | 2011-04-06 | 卡特彼勒公司 | Bearing arrangement for a pump |
| CN102003383B (en) * | 2009-08-27 | 2015-09-16 | 卡特彼勒公司 | For the bearing arrangement of pump |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C15 | Extension of patent right duration from 15 to 20 years for appl. with date before 31.12.1992 and still valid on 11.12.2001 (patent law change 1993) | ||
| RN01 | Renewal of patent term | ||
| C53 | Correction of patent of invention or patent application | ||
| COR | Change of bibliographic data |
Free format text: CORRECT: PATENTEE ADDRESS; FROM: MACHINE REPAIR WORKSHOP, ZUNYI TITANIUM FACTORY,ZUNYI CITY,GUIZHOUPROVINCE TO: NO. 2, FU, UNIT 3, NO. 2, YAONING LANE, ZIYIN ROAD, ZUNYI CITY, GUIZHOU PROVINCE |
|
| CP03 | Change of name, title or address |
Address after: No. 3, unit 2, Yao Ning lane, 2 Yin Zi Road, Guizhou, Zunyi Patentee after: Cai Wanyi Address before: Zunyi Zunyi Guizhou titanium factory machine repair shop Patentee before: Cai Wanyi |
|
| C17 | Cessation of patent right | ||
| CX01 | Expiry of patent term |