CN209419401U - A kind of turbojet engine built-in power generation structure - Google Patents
A kind of turbojet engine built-in power generation structure Download PDFInfo
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- CN209419401U CN209419401U CN201822209258.9U CN201822209258U CN209419401U CN 209419401 U CN209419401 U CN 209419401U CN 201822209258 U CN201822209258 U CN 201822209258U CN 209419401 U CN209419401 U CN 209419401U
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- axle sleeve
- inner casing
- baffle
- main shaft
- rotor
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Abstract
The utility model relates to a kind of turbojet engine built-in power generation structures, including turbine, compressor rotor, it is connected between the turbine and compressor rotor by engine spindle, generator amature is set on the outerface of spindle, in the outside of main shaft, axle sleeve is set, generator unit stator is set on the inside of axle sleeve, and the generator amature is oppositely arranged with generator unit stator.The axle sleeve includes axle sleeve shell and axle sleeve inner casing, and there are gaps between the axle sleeve shell and axle sleeve inner casing, fuel feed hole and oil return hole is arranged on the end face of axle sleeve front end, setting rotor jacket is wrapped up rotor on the outside of the rotor.The utility model is compared with prior art, it is provided with power generator in traditional turbojet engine, its electric energy generated can adequately meet the electric power needs of air craft carried equipment, and the axial dimension of engine does not change, and it is using fuel oil as cooling way, without in addition installing cooling equipment additional, manufacturing cost is also accordingly reduced.
Description
Technical field
It is more particularly to a kind of to start not changing the utility model relates to a kind of turbojet engine electrification structure
Under the premise of machine aeroperformance, generator is turned into the built-in power generation structure that stator is placed between engine compressor and turbine,
It solves the problems, such as that engine interior generator is cooling again, is particularly suitable for small-size turbojet engine field.
Background technique
With the development of turbojet engine technical level, engine is giving type cruise vehicle (predominantly unmanned plane, target
Machine, cruise missile etc.) while power is provided, also need to provide for airborne (or missile-borne, hereinafter referred to as airborne) equipment continual and steady
Power supply.Generator extracts shaft work from turbojet engine rotor system and is converted into electric energy.Since engine interior structure space is close, temperature
Degree is high, and domestic and international traditional design scheme is preposition by generator, i.e., generator is in engine inlets inside or front end, this
The shortcomings that way is the axial dimension that will increase engine, while influencing the air inlet performance of engine.Currently, removing U.S. LOCASS
Cruise missile engine J45 outside, there is no related application example using built-in power generation technology (technology blockage).
Summary of the invention
The utility model is directed to the shortcomings that preposition power generation, proposes a kind of built-in power generation structure, focuses on solving in engine
Portion's generator cools down problem, and successfully realizes 1kw power generation.
The utility model is realized using following technological means: a kind of turbojet engine built-in power generation structure, including turbine, pressure
Mechanism of qi rotor is connected by engine spindle between the turbine and compressor rotor, generator is arranged on the outerface of spindle
Rotor is arranged axle sleeve in the outside of main shaft, generator unit stator, the generator amature and generator unit stator is arranged on the inside of axle sleeve
It is oppositely arranged.The axle sleeve includes axle sleeve shell and axle sleeve inner casing, there are gap between the axle sleeve shell and axle sleeve inner casing,
Fuel feed hole and oil return hole are set on the end face of axle sleeve front end, and the fuel feed hole connects fuel tank, oil outlet and engine oil spout
System connection, the rotor outside setting rotor jacket are wrapped up rotor.
In the front end of the axle sleeve, motor outlet wire hole is set, bearing is arranged in the axle sleeve both ends,
In the rear end of axle sleeve, setting castor tooth covers and castor tooth is sealed axle sleeve shell and the rear portion of axle sleeve inner casing.
Several baffles are set on the outer surface of axle sleeve inner casing, the baffle is configured with axle sleeve inner casing length direction,
The length of baffle is less than the length of axle sleeve inner casing, and baffle is divided into first baffle and second baffle, and first baffle and second baffle are handed over
For setting, the front end of the left end connecting bushing inner casing of first baffle, the rear end of the right end connecting bushing inner casing of second baffle.
The main shaft is divided into the first main shaft connecting with turbine and the second main shaft connecting with compressor rotor, and described first
Groove is arranged in main shaft free end, and the groove extends internally, and the free end of second main shaft is protruded into groove, the first main shaft with
Second main shaft is fixedly connected.
The utility model compared with prior art, is provided with power generator in traditional turbojet engine, generates
Electric energy can adequately meet the electric power needs of air craft carried equipment, and the axial dimension of engine does not change, and its
Using fuel oil as cooling way, without in addition installing cooling equipment additional, manufacturing cost is also accordingly reduced.
Detailed description of the invention
Fig. 1 is the electrification structure schematic diagram of the utility model.
Fig. 2 is the utility model axle sleeve lateral plan.
Fig. 3 is the sleeve assembly structure chart of the utility model.
Fig. 4 is the fuel oil coolant flow channel structure chart of the utility model.
Wherein 1- turbine, 2, axle sleeve shell, 3- axle sleeve inner casing, 4- motor stator, 5- rotor sheath, 6- motor turn
Son, 7- compressor rotor, 8- bearing, 9- engine spindle, 10- castor tooth set, 11- fuel feed hole, 12- oil return hole, 13- bearing bleed
Hole, 14- baffle.
Specific embodiment
The utility model is described in further detail below:
A kind of turbojet engine built-in power generation structure of the utility model, including turbine 1, axle sleeve, motor stator 4, motor
Rotor jacket 5, rotor 6, compressor rotor 7, bearing 8, engine spindle 9, castor tooth cover 10, castor tooth 11, the compressor
It is generator for mechanical work that rotor 7, bearing 8, engine spindle 9, turbine 1, which combine and form traditional turbojet engine,.The axis
Set, 10 composition generator unit stator system of motor stator 4, castor tooth set, the rotor sheath 5, rotor 6, engine spindle 9
Combination Welding forms generator amature system, is used for cutting magnetic induction line.Generator unit stator system and generator amature system cooperate dynamic
Make, to export energy.
Wherein, sleeve assembly is formed by Combined machining after axle sleeve shell 2, the welding of axle sleeve inner casing 3, motor stator 4 and axle sleeve
Component is gap-matched, and is positioned using pin；The outside of engine spindle 9 is arranged in rotor 6, outside rotor 6
Rotor sheath 5 is welded to protect electronics rotor in side.
In the utility model, fuel feed hole 11 and oil return hole 12 are set on the end face of axle sleeve front end, the fuel feed hole 11 connects
BOR Bunker of Redelivery case, oil outlet 12 are connect with engine injection system, and fuel oil is utilized as refrigerant in the utility model, it is not required to first
Additional refrigerant material is used, a set of coolant circulating system is saved；Secondly the fuel oil being discharged from axle sleeve is with certain temperature
Degree, is easy to be ignited, high combustion efficiency, energy utilization rate is good.
Two bearings are set at the both ends of axle sleeve in the utility model, two bearings are arranged in the inside of axle sleeve, pass through axis
The friction for reducing main shaft 9 and axle sleeve inner casing 3 is held, since bearing working environment temperature is higher, in order to guarantee the normal use of bearing,
Bearing bleed hole 13 is set in former and later two end faces of axle sleeve, specifically, the bearing bleed hole 13 is arranged in axle sleeve
The end of 3 two sides of inner casing is arranged around radiuses such as ends, and is placed equidistant between bearing bleed hole 13, the utility model
Described in bearing bleed hole 13 be arranged 8,13 diameter of bearing bleed hole be 1mm.
In the utility model, several baffles 14 are set on the outer surface of the axle sleeve inner casing 3, the baffle 14 is with axle sleeve
Inner casing length direction is configured, and the length of baffle is less than the length of axle sleeve inner casing, and baffle is divided into first baffle and second baffle,
First baffle is arranged alternately with second baffle, the front end of the left end connecting bushing inner casing 3 of first baffle, and the right end of second baffle connects
Spindle covers the rear end of inner casing 3, and above-mentioned baffle constitutes fuel oil coolant flow channel, extends fuel oil residence time in axle sleeve,
It enables fuel oil that can adequately absorb the temperature in axle sleeve, reaches the maximization of cooling.
In the front end of the axle sleeve, setting motor outlet wire hole supply lines is pierced by, and in the rear end of axle sleeve, setting castor tooth covers 10 and castor
Tooth is sealed axle sleeve shell 2 and the rear portion of axle sleeve inner casing 3, and enabling becomes a seal in axle sleeve, and fuel oil is enabled not leak.
The main shaft 9 divides for the first main shaft connecting with turbine and the second main shaft connecting with compressor rotor, and described
Groove is arranged in one main shaft free end, and the groove extends internally, and the free end of second main shaft is protruded into groove, the first main shaft
It is fixedly connected with the second main shaft.It is set as after two sections, enables the replacement of main shaft more convenient, while also reducing the entirety of main shaft
Weight.
Claims (7)
1. a kind of turbojet engine built-in power generation structure, including turbine, compressor rotor, between the turbine and compressor rotor
It is connected by engine spindle, it is characterised in that: generator amature is set on the outerface of spindle, axis is set in the outside of main shaft
Set, is arranged generator unit stator, the generator amature is oppositely arranged with generator unit stator on the inside of axle sleeve.
2. turbojet engine built-in power generation structure according to claim 1, it is characterised in that: the axle sleeve includes axle sleeve
Shell and axle sleeve inner casing, there are gaps between the axle sleeve shell and axle sleeve inner casing, and oil inlet is arranged on the end face of axle sleeve front end
Hole and oil return hole, the fuel feed hole connect fuel tank, and oil outlet is connect with engine injection system.
3. turbojet engine built-in power generation structure according to claim 1, it is characterised in that: setting on the outside of the rotor
Rotor jacket is wrapped up rotor.
4. turbojet engine built-in power generation structure according to claim 1, it is characterised in that: set in the front end of the axle sleeve
Motor outlet wire hole is set, bearing is arranged in the axle sleeve both ends, and bearing bleed hole is arranged in former and later two end faces of axle sleeve.
5. turbojet engine built-in power generation structure according to claim 1, it is characterised in that: castor is arranged in the rear end of axle sleeve
Tooth set and castor tooth are sealed axle sleeve shell and the rear portion of axle sleeve inner casing.
6. turbojet engine built-in power generation structure according to claim 2, it is characterised in that: in the outer surface of axle sleeve inner casing
Upper several baffles of setting, the baffle are configured with axle sleeve inner casing length direction, and the length of baffle is less than the length of axle sleeve inner casing
Degree, baffle are divided into first baffle and second baffle, and first baffle is arranged alternately with second baffle, the left end connecting shaft of first baffle
Cover the front end of inner casing, the rear end of the right end connecting bushing inner casing of second baffle.
7. turbojet engine built-in power generation structure according to claim 1, it is characterised in that: the main shaft is divided into and turbine
First main shaft of connection and the second main shaft connecting with compressor rotor, groove is arranged in first main shaft free end, described recessed
Slot extends internally, and the free end of second main shaft is protruded into groove, and the first main shaft is fixedly connected with the second main shaft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822209258.9U CN209419401U (en) | 2018-12-27 | 2018-12-27 | A kind of turbojet engine built-in power generation structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822209258.9U CN209419401U (en) | 2018-12-27 | 2018-12-27 | A kind of turbojet engine built-in power generation structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209419401U true CN209419401U (en) | 2019-09-20 |
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ID=67939258
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201822209258.9U Active CN209419401U (en) | 2018-12-27 | 2018-12-27 | A kind of turbojet engine built-in power generation structure |
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| Country | Link |
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| CN (1) | CN209419401U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110554318A (en) * | 2019-09-27 | 2019-12-10 | 贵州航天林泉电机有限公司 | High-speed alternating-current generator test bed considering speed regulation interval |
-
2018
- 2018-12-27 CN CN201822209258.9U patent/CN209419401U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110554318A (en) * | 2019-09-27 | 2019-12-10 | 贵州航天林泉电机有限公司 | High-speed alternating-current generator test bed considering speed regulation interval |
| CN110554318B (en) * | 2019-09-27 | 2021-08-27 | 贵州航天林泉电机有限公司 | High-speed alternating-current generator test bed considering speed regulation interval |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20230724 Address after: 210026 3rd Floor, Comprehensive Experimental Building, No.1 Science and Technology Innovation Avenue, Lishui Economic Development Zone, Nanjing, Jiangsu Province Patentee after: Rongtong Aviation Engine Technology Co.,Ltd. Address before: No. 766, Zhujiang Road, Nanjing, Jiangsu, 210016 Patentee before: NO.60 INSTITUTE OF THE HEADQUARTERS OF GENERAL STAFF OF PLA |
|
| TR01 | Transfer of patent right |