CN103047068A - Composite type turbine air starter - Google Patents
Composite type turbine air starter Download PDFInfo
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- CN103047068A CN103047068A CN2012105151070A CN201210515107A CN103047068A CN 103047068 A CN103047068 A CN 103047068A CN 2012105151070 A CN2012105151070 A CN 2012105151070A CN 201210515107 A CN201210515107 A CN 201210515107A CN 103047068 A CN103047068 A CN 103047068A
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Abstract
The invention discloses a composite type turbine air starter which comprises a machine body (4) and is characterized in that the machine body (4), a fixed wheel (1), an inner gear (7) and a cylinder (9) are connected together, and a piston (10) is arranged in between the inner gear (7) and the cylinder (9); a guiding impeller (5) is arranged in the machine body (4), a rotor shaft (15) is arranged at the center of the machine body, a movable wheel (2) is arranged at the left end of the rotor shaft (15), and the right end of the rotor shaft (15) is in gear meshing with a planetary gear (6) on a planet carrier assembly (8); an output gear assembly (12) is sleeved outside the planet carrier assembly (8) and arranged on the cylinder (9), and a reset spring (11) is arranged between the output gear assembly (12) and the cylinder (9); a primary axial turbine gear (19), a secondary radial turbine gear (21) and a tertiary radial turbine gear (23) are arranged on the movable wheel (2), a primary guide blade air distribution groove (18) is arranged on the guiding impeller (5), and a secondary guide blade air distribution groove (20) and a tertiary guide blade air distribution groove (22) are arranged on the fixed wheel (1). The starter is low in noise and long in service life, simplifies a diesel starting system and omits regular oiling maintenance.
Description
Technical field:
The present invention relates to the pneumatic machinery technical field, is a kind of combined type turbine gas starter concretely, is used for diesel engine and starts.
Background technique:
Power marine diesel engine in the 80HP-4000HP scope extensively adopts the starting of gas starter at present, and the power section of traditional gas starter is vane type motor, and it is lubricated to add oil sprayer, and oil sprayer oil is consumptive, must safeguard by intermittent oiling.The exhaust outlet noise is large in addition, needs to be equipped with special-purpose silencing apparatus.Under the winter cryogenic conditions, the lubricant oil thickness easily causes blade to be bonded in the rotor not throwing away, cause motor failure.Expand in high temperature wet condition lower blade drinking water and to cause motor stuck and lost efficacy.The common problem that this blade gas starter exists is: system's accessory is many, and it is large to take up space, and the incipient fault rate is high, and the life-span is short.
Summary of the invention:
The objective of the invention is to overcome the deficiency of above-mentioned prior art, and a kind of turbo type gas starter is provided, mainly solve the problems such as existing blade gas actuator system accessory is many, take up space large, incipient fault rate height and life-span are short.
Technological scheme of the present invention is: a kind of combined type turbine gas starter, and it comprises body, and its special way is the both sides of body respectively by V-arrangement clip connected fixed wheel and internal gear, and internal gear and cylinder link together, and establish piston between internal gear and cylinder; In body, establish guide vane wheel; On internal gear, connect planetary wheel carrier assembly middle part by bearing, planetary wheel carrier assembly right-hand member is supported on the cylinder, establish planetary pinion at the planetary wheel carrier assembly, the two is slidingly matched, planetary external tooth and the engagement of internal gear gear, the right-hand member gear engagement of the rotor shaft of planetary external tooth and body center, the left end of rotor shaft is installed driving wheel, between the two interference fit joint; Establish output gear component in cylinder, output gear component is enclosed within outside the planetary wheel carrier assembly, establishes Returnning spring between output gear component and cylinder; Establish the axial turbo tooth of the first order, second level radial turbine tooth and third level radial turbine tooth at driving wheel, establish second level stator gas booking groove and third level stator gas booking groove at fixed wheel.
Compared with the prior art a kind of combined type turbine gas starter of the present invention has outstanding substantive distinguishing features and remarkable progress: 1, power section is made of three grades of turbo type motors, first grade axis is set to turbine and two-stage radial turbine in less space, three grades of turbines are realized by stator, driving wheel and three parts of fixed wheel, level of integration is high, compare vane type motor, same summation watt rating is larger; 2, the starter noise is low, need not to dispose silencing apparatus, has simplified the diesel engine starting system; 3, turbine does not does not wear and tear in using, and therefore compares the blade gas starter, and this life of product is longer, needing in diesel engine to be more suitable for the occasion of Fraquent start; 4, compare the blade gas starter, this starter need not to dispose oil sprayer, has simplified diesel engine starting system, and removes intermittent oiling from and safeguard.
Fig. 1 is main TV structure schematic representation of the present invention;
Fig. 2 is the axial turbine schematic representation of the first order of the present invention;
Fig. 3 is second and third grade radial turbine schematic representation of the present invention.
The drawing explanation:
1 fixed wheel, 2 driving wheels, 3 V-arrangement clips, 4 bodies, 5 guide vane wheels, 6 planetary pinions, 7 internal gears, 8 planetary wheel carrier assemblies, 9 cylinders, 10 pistons, 11 Returnning springs, 12 output gear components, 13 screws, 14 clutch shaft bearings, 15 rotor shafts, 16 second bearings, 17 the 3rd bearings, 18 chopped-off head stator gas booking grooves, the axial turbo tooth of 19 first order, 20 second level stator gas booking grooves, 21 second level radial turbine teeth, 22 third level stator gas booking grooves, 23 third level radial turbine teeth.
Embodiment:
For Comprehension and Implementation better, provide specific embodiment below in conjunction with accompanying drawing and describe in detail.
Embodiment 1, referring to Fig. 1,2,3, is processed into body 4, connects fixed wheel 1 and internal gear 7 by V-arrangement clip 3 respectively in the both sides of body 4, with screw 13 internal gear 7 and cylinder 9 is linked together, and piston 10 is installed between internal gear 7 and cylinder 9; At body 4 interior installation guide vane wheels 5, the two is threaded connection; Rotor shaft 15 is installed by the second bearing 16 and the 3rd bearing 17 in center at body 4, at the left end of rotor shaft 15 driving wheel 2, between the two interference fit joint is installed; Support planetary wheel carrier assembly 8 middle parts at internal gear 7 by clutch shaft bearing 14, the right-hand member of planetary wheel carrier assembly 8 is supported on the cylinder 9, at planetary wheel carrier assembly 8 planetary pinion 6 is installed, the two is slidingly matched, the external tooth of planetary pinion 6 and the engagement of internal gear 7 gears, the right-hand member gear engagement of the external tooth of planetary pinion 6 and rotor shaft 15; Output gear component 12 is enclosed within is contained on the planetary wheel carrier assembly 8 in the cylinder 9, Returnning spring 11 is installed between output gear component 12 and cylinder 9; At the axial turbo tooth 19 of the driving wheel 2 processing first order, second level radial turbine tooth 21 and third level radial turbine tooth 23, at guide vane wheel 5 processing chopped-off head stator gas booking grooves 18, at fixed wheel 1 processing second level stator gas booking groove 20 and third level stator gas booking groove 22; Be assembled into a kind of combined type turbine gas starter of the present invention.
A kind of combined type turbine gas starter of the present invention, the generation of power realizes in the following manner: pressurized air is entered in the body by the P1 mouth, change into unidirectional high-pressure air stream by chopped-off head stator gas booking groove and blow to the axial turbo tooth of the first order, by the axial turbo tooth of the first order driving wheel is rotated, again change into unidirectional high-pressure air stream from the high-pressure air stream of the axial turbo tooth outflow of the first order by secondary stator gas booking groove and blow to second level radial turbine tooth, again produce the power that driving wheel is rotated by second level radial turbine tooth, change into for the third time unidirectional high-pressure air stream from the high-pressure air stream of second level radial turbine tooth outflow by third level stator gas booking groove and blow to third level radial turbine tooth, produce for the third time the power that driving wheel is rotated by third level radial turbine tooth.Pressurized air at last by the P2 mouth discharged to atmosphere, driving wheel rotor driven axle rotates, planet wheel decelerator by planetary pinion, internal gear, planetary wheel carrier module composition, the planetary wheel carrier assembly is rotated, be provided with involute splines between planetary wheel carrier assembly and the output gear component, rotate thereby drive output gear component, by the output gear component outputting power.
Output gear component moves through following mode and realizes: pressurized air is entered in the cylinder by the P3 mouth, and pushing piston and output gear component move right, simultaneously compression reseting spring; After P3 mouth pressurized air was removed, Returnning spring pushing piston and output gear component moved left and put in place.
Claims (1)
1. combined type turbine gas starter, it comprises body (4), the both sides that it is characterized in that body (4) connect fixed wheel (1) and internal gear (7) by V-arrangement clip (3) respectively, internal gear (7) links together with cylinder (9), establishes piston (10) between internal gear (7) and cylinder (9); In body (4), establish guide vane wheel (5); Upper by bearing connection planetary wheel carrier assembly (8) middle part at internal gear (7), the right-hand member of planetary wheel carrier assembly (8) is supported on the cylinder (9), establish planetary pinion (6) at planetary wheel carrier assembly (8), the two is slidingly matched, the external tooth of planetary pinion (6) and the engagement of internal gear (7) gear, the right-hand member gear engagement of the rotor shaft (15) at the external tooth of planetary pinion (6) and body (4) center, the left end of rotor shaft (15) is installed driving wheel (2), between the two interference fit joint; Establish output gear component (12) in cylinder (9), output gear component (12) is enclosed within outside the planetary wheel carrier assembly (8), establishes Returnning spring (11) between output gear component (12) and cylinder (9); Establish the axial turbo tooth of the first order (19), second level radial turbine tooth (21) and third level radial turbine tooth (23) at driving wheel (2), establish chopped-off head stator gas booking groove (18) at guide vane wheel (5), establish second level stator gas booking groove (20) and third level stator gas booking groove (22) at fixed wheel (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012105151070A CN103047068A (en) | 2012-12-05 | 2012-12-05 | Composite type turbine air starter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012105151070A CN103047068A (en) | 2012-12-05 | 2012-12-05 | Composite type turbine air starter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103047068A true CN103047068A (en) | 2013-04-17 |
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ID=48059861
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2012105151070A Pending CN103047068A (en) | 2012-12-05 | 2012-12-05 | Composite type turbine air starter |
Country Status (1)
| Country | Link |
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| CN (1) | CN103047068A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103821566A (en) * | 2014-02-08 | 2014-05-28 | 华南理工大学 | Air starting motor with switchable single turbine and double turbines |
| CN109113909A (en) * | 2017-06-22 | 2019-01-01 | 襄阳联航动力技术有限公司 | A kind of internal combustion engine Pneumatic starting system |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4830571A (en) * | 1986-02-24 | 1989-05-16 | Tech Development Inc. | Pneumatic starters |
| CN2302347Y (en) * | 1997-01-29 | 1998-12-30 | 中国船舶工业总公司第七研究院第七一一研究所 | Turbogas starting motor |
| CN2828352Y (en) * | 2004-03-05 | 2006-10-18 | 姜世英 | High power strength turbo gas starting motor |
| CN101328852A (en) * | 2008-07-25 | 2008-12-24 | 煤炭科学研究总院太原研究院 | Turbine type gas starting equipment of diesel engine |
| CN202971002U (en) * | 2012-12-05 | 2013-06-05 | 烟台卡伦特机械制造有限公司 | Compound-type turbine gas starter |
-
2012
- 2012-12-05 CN CN2012105151070A patent/CN103047068A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4830571A (en) * | 1986-02-24 | 1989-05-16 | Tech Development Inc. | Pneumatic starters |
| CN2302347Y (en) * | 1997-01-29 | 1998-12-30 | 中国船舶工业总公司第七研究院第七一一研究所 | Turbogas starting motor |
| CN2828352Y (en) * | 2004-03-05 | 2006-10-18 | 姜世英 | High power strength turbo gas starting motor |
| CN101328852A (en) * | 2008-07-25 | 2008-12-24 | 煤炭科学研究总院太原研究院 | Turbine type gas starting equipment of diesel engine |
| CN202971002U (en) * | 2012-12-05 | 2013-06-05 | 烟台卡伦特机械制造有限公司 | Compound-type turbine gas starter |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103821566A (en) * | 2014-02-08 | 2014-05-28 | 华南理工大学 | Air starting motor with switchable single turbine and double turbines |
| CN109113909A (en) * | 2017-06-22 | 2019-01-01 | 襄阳联航动力技术有限公司 | A kind of internal combustion engine Pneumatic starting system |
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Application publication date: 20130417 |