CN109301998A - A kind of aircraft fluid circuit electric motor for pump seal stator structure - Google Patents
A kind of aircraft fluid circuit electric motor for pump seal stator structure Download PDFInfo
- Publication number
- CN109301998A CN109301998A CN201811391143.4A CN201811391143A CN109301998A CN 109301998 A CN109301998 A CN 109301998A CN 201811391143 A CN201811391143 A CN 201811391143A CN 109301998 A CN109301998 A CN 109301998A
- Authority
- CN
- China
- Prior art keywords
- casing
- shroud sleeve
- fluid circuit
- stator
- electric motor
- 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.)
- Pending
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Classifications
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K9/00—Arrangements for cooling or ventilating
- H02K9/19—Arrangements for cooling or ventilating for machines with closed casing and closed-circuit cooling using a liquid cooling medium, e.g. oil
- H02K9/197—Arrangements for cooling or ventilating for machines with closed casing and closed-circuit cooling using a liquid cooling medium, e.g. oil in which the rotor or stator space is fluid-tight, e.g. to provide for different cooling media for rotor and stator
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K5/00—Casings; Enclosures; Supports
- H02K5/04—Casings or enclosures characterised by the shape, form or construction thereof
- H02K5/10—Casings or enclosures characterised by the shape, form or construction thereof with arrangements for protection from ingress, e.g. water or fingers
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K5/00—Casings; Enclosures; Supports
- H02K5/04—Casings or enclosures characterised by the shape, form or construction thereof
- H02K5/12—Casings or enclosures characterised by the shape, form or construction thereof specially adapted for operating in liquid or gas
Landscapes
- Engineering & Computer Science (AREA)
- Power Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses a kind of aircraft fluid circuit electric motor for pump seal stator structures, including shroud sleeve, casing, armature stator and rear end cap, shroud sleeve and casing constitute inner-cooling structure, armature stator is arranged between shroud sleeve and casing, and the end of shroud sleeve is arranged in rear end cap and casing constitutes sealing structure.Fluid circuit pump brushless direct current motor that the present invention designs and pump ontology have carried out integrated design, stationary seal in design, have many advantages, such as compact-sized, the high efficiency, long-life, highly reliable.
Description
Technical field
The invention belongs to DC motor technology fields, and in particular to cold brushless in a kind of long-life, highly reliable, high leakproofness
Dc motor seal stator structure.
Background technique
Fluid circuit circulating pump is worked under space environment with interior cold brushless direct current motor (hereinafter referred to as motor), motor
Around belong near vacuum state, heat when motor longtime running inside motor can only be by external radiation and solid or liquid
Contact calorie spread is gone out.Under no good cooling condition, power density (power density of the motor in space environment
=power/quality) far smaller than in ground air environment.
The principal element of General Influence electrical machinery life is the nonmetallic materials service life, and nonmetallic materials can occur always at any time
Change, is rotten, it is most likely that influencing the sealing performance of motor, or even cause seal failure and then influence the service life of product.
Summary of the invention
In view of the above-mentioned deficiencies in the prior art, the technical problem to be solved by the present invention is that providing a kind of aircraft stream
Body loop pump motor stator sealing structure can solve the close brshless DC motor degree heat dissipation problem of spacecraft pump high power again
Motor be can solve in the integrity problem of 15 older lifetime inner seal structures.
The invention adopts the following technical scheme:
A kind of aircraft fluid circuit electric motor for pump seal stator structure, including shroud sleeve, casing, armature stator and after
End cap, shroud sleeve and casing constitute inner-cooling structure, and armature stator is arranged between shroud sleeve and casing, and rear end cap setting exists
The end of shroud sleeve and casing constitute sealing structure.
Specifically, casing is arranged on shroud sleeve, airtight cavity is formed between shroud sleeve, armature stator is located at close
In closed chamber body.
Further, potting compound is provided between armature stator and shroud sleeve, casing and rear end cap.
Further, shroud sleeve, casing, armature stator and rear end cap encapsulating are integrated by potting compound using encapsulating mode
Structure.
Further, the gap of armature laundry shroud sleeve and casing is 0.45~0.55mm in airtight cavity.
Specifically, shroud sleeve is an integral structure.
Further, shroud sleeve is prepared using titanium alloy.
Compared with prior art, the present invention at least has the advantages that
Armature stator is formed a complete reliably inner cavity by the present invention, can greatly improve motor leakproofness and
Reliability, and overall stiffness is increased using encapsulating structure, it is convenient for the ultra-thin processing of armature portion shroud sleeve, reduces in housing
Eddy-current loss.It has applied, has worked well on multiple spacecrafts at present.
Further, shroud sleeve, casing, armature stator and rear end cap encapsulating are formed one completely using encapsulating mode
Reliable inner cavity can greatly improve the rigidity of motor stator, improve the bearing capacity of stator.
Further, the purpose of setting that shroud sleeve is an integral structure is the core part of motor stator sealing, is used
Integral structure is cut down the number of intermediate links, and reliability is improved, and extends the service life.
Further, shroud sleeve using titanium alloy bar fabricate, by using encapsulating structure increase integral strength and
Rigidity controls shroud sleeve armature portion thickness and installation using secondary operation mode for the eddy-current loss for reducing shroud sleeve
Position portion size improves the corrosion resistance of shroud sleeve simultaneously because titanium alloy resistivity is higher, can reduce housing
The loss of cylinder improves system effectiveness.
In conclusion the fluid circuit pump that the present invention designs has carried out integrated set with brushless direct current motor with pump ontology
Meter, stationary seal in design have many advantages, such as compact-sized, the high efficiency, long-life, highly reliable.
Below by drawings and examples, technical scheme of the present invention will be described in further detail.
Detailed description of the invention
Fig. 1 is integral type shroud sleeve structural schematic diagram；
Fig. 2 is sealed structural schematic diagram.
Wherein: 1. shroud sleeves；2. casing；3. armature stator；4. potting compound；5. rear end cap.
Specific embodiment
In the description of the present invention, it is to be understood that, term " center ", " longitudinal direction ", " transverse direction ", "upper", "lower",
"front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outside", " side ", " one end ", " one side " etc.
The orientation or positional relationship of instruction is to be based on the orientation or positional relationship shown in the drawings, and is merely for convenience of the description present invention and letter
Change description, rather than the device or element of indication or suggestion meaning must have a particular orientation, with specific orientation construct and
Operation, therefore be not considered as limiting the invention.
In the description of the present invention, it should be noted that unless otherwise clearly defined and limited, term " installation ", " phase
Even ", " connection " shall be understood in a broad sense, for example, it may be being fixedly connected, may be a detachable connection, or be integrally connected；It can
To be mechanical connection, it is also possible to be electrically connected；It can be directly connected, can also can be indirectly connected through an intermediary
Connection inside two elements.For the ordinary skill in the art, above-mentioned term can be understood at this with concrete condition
Concrete meaning in invention.
The present invention provides a kind of aircraft fluid circuit electric motor for pump seal stator structure, using brushless motor stator,
Inner-cooling structure and sealing structure.Can be applied to the long-life, it is highly reliable and with high leakproofness require spacecraft on, using this
The brushless direct current motor that technology manufactures can work under space environment, with small in size, power is big, leak rate is low and the service life
The features such as long.
Please refer to Fig. 1 and Fig. 2, a kind of aircraft fluid circuit electric motor for pump seal stator structure of the present invention, including one
Formula shroud sleeve 1, casing 2, armature stator 3, potting compound 4 and rear end cap 5；Casing 2 is arranged on integral shielding sleeve 1, with
Airtight cavity is formed between integral shielding sleeve 1, armature stator 3 is sleeved on integral shielding sleeve 1, is located at airtight cavity
Interior, one end of integral shielding sleeve 1 is arranged in rear end cap 5, and potting compound 4 is arranged in airtight cavity, integral shielding sleeve
1, it is connected between casing 2, armature stator 3 and rear end cap 5 by potting compound 4.
In one integrated metal shroud sleeve 1 of motor stator end cap and bore design.Using dosing technology by integral type
Shroud sleeve 1, casing 2, armature stator 3 improve the strength and stiffness of integral shielding sleeve 1 together with 4 encapsulating of rear end cap,
Reach long-life, highly reliable, low-loss feature.
The ingredient potting compound of potting compound 4 is High temperature epoxy resins material.
Integrated metal shroud sleeve 1 is manufactured using titanic alloy machining.
(1) electromagnetic scheme that motor is designed according to motor performance need to estimate housing loss；
(2) integral type titanium alloy shroud sleeve is processed, reserves 0.5mm in armature portion；
(3) casing 2, armature stator 3, integral shielding sleeve 1 and rear end cap 5 are fitted together；
(4) with epoxy resin by casing 2, armature stator 3, integral shielding sleeve 1 and 5 encapsulating of rear end cap together；
(5) armature portion shroud sleeve is processed to 0.45~0.55mm.
The present invention is aircraft fluid circuit electric motor for pump, and motor driven impeller provides circulation power for cycle fluid.It is logical
Integrated design thinking is crossed, is guaranteeing that will recycle a part of working medium while being provided out enough flows and pressure introduces motor
Inside is cooled down for motor.The gross mass of working medium in spacecraft has strict demand, therefore it is required that in entire fluid space
It is required that there is higher leakproofness.With the development of China's aerospace industry, the service life of motor is required higher and higher.
The above content is merely illustrative of the invention's technical idea, and this does not limit the scope of protection of the present invention, all to press
According to technical idea proposed by the present invention, any changes made on the basis of the technical scheme each falls within claims of the present invention
Protection scope within.
Claims (7)
1. a kind of aircraft fluid circuit electric motor for pump seal stator structure, which is characterized in that including shroud sleeve (1), casing
(2), armature stator (3) and rear end cap (5), shroud sleeve (1) and casing (2) constitute inner-cooling structure, and armature stator (3) setting exists
Between shroud sleeve (1) and casing (2), rear end cap (5), which is arranged, constitutes sealing knot in the end of shroud sleeve (1) and casing (2)
Structure.
2. aircraft fluid circuit electric motor for pump seal stator structure according to claim 1, which is characterized in that casing
(2) it is arranged on shroud sleeve (1), forms airtight cavity between shroud sleeve (1), armature stator (3) is located at airtight cavity
It is interior.
3. aircraft fluid circuit electric motor for pump seal stator structure according to claim 1 or 2, which is characterized in that electricity
Potting compound (4) are provided between pivot stator (3) and shroud sleeve (1), casing (2) and rear end cap (5).
4. aircraft fluid circuit electric motor for pump seal stator structure according to claim 3, which is characterized in that potting compound
(4) shroud sleeve (1), casing (2), armature stator (3) and rear end cap (5) encapsulating are structure as a whole using encapsulating mode.
5. aircraft fluid circuit electric motor for pump seal stator structure according to claim 2, which is characterized in that closed chamber
The gap of shroud sleeve (1) and casing (2) is 0.45~0.55mm at internal armature stator (3).
6. aircraft fluid circuit electric motor for pump seal stator structure according to claim 1, which is characterized in that housing
Cylinder (1) is an integral structure.
7. aircraft fluid circuit electric motor for pump seal stator structure according to claim 6, which is characterized in that housing
Cylinder (1) is prepared using titanium alloy.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811391143.4A CN109301998A (en) | 2018-11-21 | 2018-11-21 | A kind of aircraft fluid circuit electric motor for pump seal stator structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811391143.4A CN109301998A (en) | 2018-11-21 | 2018-11-21 | A kind of aircraft fluid circuit electric motor for pump seal stator structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109301998A true CN109301998A (en) | 2019-02-01 |
Family
ID=65144561
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811391143.4A Pending CN109301998A (en) | 2018-11-21 | 2018-11-21 | A kind of aircraft fluid circuit electric motor for pump seal stator structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109301998A (en) |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3831457A1 (en) * | 1988-09-16 | 1990-03-22 | Licentia Gmbh | Electric motor-driven fluid pump |
| CN2495052Y (en) * | 2001-09-07 | 2002-06-12 | 张云 | Open type shield submersible electric motor |
-
2018
- 2018-11-21 CN CN201811391143.4A patent/CN109301998A/en active Pending
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3831457A1 (en) * | 1988-09-16 | 1990-03-22 | Licentia Gmbh | Electric motor-driven fluid pump |
| CN2495052Y (en) * | 2001-09-07 | 2002-06-12 | 张云 | Open type shield submersible electric motor |
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|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20190201 |