CN104963731B - Novel aero-engine thermal compensation structure - Google Patents
Novel aero-engine thermal compensation structure Download PDFInfo
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- CN104963731B CN104963731B CN201510191104.XA CN201510191104A CN104963731B CN 104963731 B CN104963731 B CN 104963731B CN 201510191104 A CN201510191104 A CN 201510191104A CN 104963731 B CN104963731 B CN 104963731B
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- Prior art keywords
- thermal compensation
- holes
- connection member
- compensation connection
- thermal
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Abstract
Provided is a novel aero-engine thermal compensation connecting structure. The structure has a similar appearance with a conventional thermal compensation structure. The structure is an annular structure whose cross section is in an S shape. The differences between the structure and the conventional structure, and characteristics of the structure are that the structure holes and a ribbed plate are added on the basis of the annular structure. The holes are long oval holes, and the shape is the shape of main holes on the thermal compensation structure. Each row of holes are staggered with the holes of the upper row and the lower row. The smaller the distance between the holes, the better the thermal insulation effect is good, but stress and rigidity are reduced. In order to make up the defect, on the basis of the holes, the ribbed plate is added on the thermal compensation structure. On the premise of ensuring strength and rigidity of the thermal compensation connecting structure to satisfy design requirements, the structure can obviously obstruct thermal transmission, and weight is reduced.
Description
Technical field
The present invention relates to a kind of aero-engine thermal compensation attachment structure, belong to aero propulsion technical field.
Background technology
Thermal compensation structure is the structure connecting rear housing and bearing block in some engine structures, and epimere is connected to load
Casing, lower end is connected with bearing block.Because before turbine, intake air temperature is very high, although rear housing can pass through structure design and cooling
System is cooling down, but temperature or to I haven't seen you for ages more than 500 DEG C, and bearing is limited due to lubrication, its normal working temperature one
As be less than 300 DEG C, both temperature difference are close to 200 DEG C.Therefore thermal compensation structure bears load and making of lowering the temperature simultaneously
Life, should have enough intensity and appropriate rigidity to support, realize cooling in small space again.
Thermal compensation structure one side will have enough intensity and appropriate rigidity to ensure to support, on the other hand again relatively
Reduce heat transfer in short distance.
Content of the invention
For the problems referred to above, it is an object of the invention to provide a kind of aero-engine thermal compensation attachment structure, this structure exists
The heat conductivility of thermal compensation attachment structure on the premise of not reducing thermal compensation attachment structure rigidity, can be reduced obviously.
According to one embodiment of present invention, thermal compensation attachment structure adopts the version that section is s, increases conduction of heat
Distance, opens long avette hole it is therefore an objective to increase thermal-conduction resistance in loop configuration.In order to ensure rigidity requirement, add in s shape structure
Floor.
A kind of profile of aero-engine thermal compensation attachment structure according to an embodiment of the invention is loop configuration,
Including on install in, lower installation, floor, circular hole and long avette hole；It is characterized in that thermal compensation attachment structure is in conventional knot
Open long avette hole on the basis of structure, added floor, its mesopore has had two kinds of shapes, hole has been long avette hole, be the most main between floor
Want is also the most hole of quantity, and each row is arranged using cross one another mode with two rows, is cooling major measure, also
There is minority circular hole, be mainly distributed on floor both sides, the gap of cover each misarrangement perforate.Floor one has 8, is distributed on annular
In structure.
The invention has the benefit that on the premise of meeting strength and stiffness design requirement, heat can be improved by a relatively large margin
Compensate the thermal conduction effect of attachment structure.
Brief description
Fig. 1 is the present invention: new aero-engine thermal compensation attachment structure；
Fig. 2 is aero-engine common thermal compensation attachment structure cooling-down effect figure；
Fig. 3 is cooling-down effect figure of the present invention；
Fig. 4 is stress envelope of the present invention.
In figure label declaration is as follows:
Side is installed on 1；2 times installation sides；3 floors；4 circular ports；5 long fourths of the twelve Earthly Branches shape hole.
Specific embodiment
The invention provides a kind of aero-engine thermal compensation attachment structure, right with reference to the accompanying drawings and detailed description
The present invention is further described.
As shown in figure 1, thermal compensation attachment structure according to an embodiment of the invention includes: above install side 1, lower installation
Side 2, floor 3, circular port 4 and long avette hole 5 form.Upper installation side 1 is connected with rear housing, and lower installation side 2 is connected with bearing block,
Because upper and lower temperature difference is larger, main body adopts the version that section is s shape it is therefore an objective to increase conduction of heat distance.Agent structure has 3
The annular region that partly can punch, two rows or three rows long avette hole is opened according to width size in each region, and each row with upper
Lower two rows mutually stagger, and, from being maintained between 3mm～5mm, distance is less, and the heat of transmission is fewer for every array pitch, and processing is got up
More difficult, the distance between Kong Yukong is maintained at 2mm～2.5mm, too little if intensity can not meet design requirement, too big if
Cooling-down effect is bad, at floor 3 due to long avette hole is staggered can not be completely the same, therefore do not have tapping to open circle
Shape hole, this kind of structure design purpose is farthest to increase thermal-conduction resistance, lowers the temperature to a greater degree.Meanwhile, in order to ensure heat
Compensate the requirement of attachment structure strength and stiffness, add 8 floors 3 in s shape ring structure, alternate 45 ° of every floor 3, circumferentially
Arrangement.Floor 3 is more wide thicker, better for increase rigidity and intensity effect, and the thermal compensation attachment structure of the present invention only needs to protect
Card strength and stiffness design requirement.
The present inventor is simulated to the cooling-down effect of this thermal compensation attachment structure analyzing: each in thermal compensation attachment structure
Individual face applies initial temperature parameter, carries out analysis of Heat Transfer, after drawing temperature field, applies axial constraint, carry out at lower installation side
Intensity analysiss.
Analysis of Heat Transfer result shows, installs side temperature (reading as 344.17 DEG C from Fig. 3) well below former knot under this structure
The corresponding temperature (reading as 400 DEG C from Fig. 2) of structure, cooling-down effect is obvious.
Fig. 4 stress analysis result display maximum stress (496.36mpa) is distributed in floor bending part, due to s shape structure originally
Carry out angle just less, add that floor is equivalent to increase thickness, lead to angle to reduce, so stress becomes big, chamfering can be passed through
Mode increases bent angle, reduces stress.In addition the stress between long avette hole increases with the reduction of pitch of holes, so pitch of holes
It is little as best one can on the premise of proof stress meets requirement.
New version is introduced, perforate, ribbed panel on the basis of agent structure in the present invention.The purpose of perforate be for
Increase the thermal-conduction resistance of structure, increase temperature drop.After perforate, the strength and stiffness of structure all decrease, and therefore increasing floor makes
Strength and stiffness meet design requirement.
Described structure has the advantage that (1) can largely reduce the temperature of thermal compensation attachment structure lower end；
(2) reduce weight and be conducive to electromotor global design.
Claims (5)
1. it is used for connecting the rear housing of aero-engine and the thermal compensation connection member of bearing block, its feature includes:
Upper installation side (1), for being connected with rear housing；
Lower installation side (2), for being connected with bearing block；
The main part of wherein said thermal compensation connection member has s tee section, has three annular regions, with increase conduction of heat away from
From；Each described annular region has platoon leader's 2-3 oval pore, the long avette hole opened along the circumferential direction equally spaced sets
Put.
2. thermal compensation connection member according to claim 1, its feature further includes:
Multiple floors (3) are circumferentially provided with described s tee section, for ensureing the intensity of thermal compensation connection member with just
Degree.
3. thermal compensation connection member according to claim 2 it is characterised in that:
Described floor (3) has eight, is circumferentially equally spaced.
4. the thermal compensation connection member according to Claims 2 or 3 it is characterised in that:
Mutually staggered with the long avette hole of two rows in the long avette hole of each row, in the described annular region close to floor (3)
Part, cannot be opened at long avette hole due to described floor (3), have circular port.
5. thermal compensation connection member according to claim 4 it is characterised in that:
The distance of every platoon leader's oval pore/circular port, between 3mm-5mm, exists with the distance between long avette hole/circular port arranged
2mm-2.5mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510191104.XA CN104963731B (en) | 2015-04-21 | 2015-04-21 | Novel aero-engine thermal compensation structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510191104.XA CN104963731B (en) | 2015-04-21 | 2015-04-21 | Novel aero-engine thermal compensation structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104963731A CN104963731A (en) | 2015-10-07 |
| CN104963731B true CN104963731B (en) | 2017-02-01 |
Family
ID=54217790
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510191104.XA Expired - Fee Related CN104963731B (en) | 2015-04-21 | 2015-04-21 | Novel aero-engine thermal compensation structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104963731B (en) |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CA1011200A (en) * | 1973-12-17 | 1977-05-31 | Yamaha Hatsudoki Kabushiki Kaisha | Small-sized snowmobile |
| US4622136A (en) * | 1985-08-23 | 1986-11-11 | Watson Karcey International | Reusable liquid filter assembly |
| US6962194B2 (en) * | 2003-11-28 | 2005-11-08 | Dana Canada Corporation | Brazed sheets with aligned openings and heat exchanger formed therefrom |
| US9140217B2 (en) * | 2012-09-06 | 2015-09-22 | Senior Ip Gmbh | Exhaust gas recirculation apparatus and method for forming same |
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2015
- 2015-04-21 CN CN201510191104.XA patent/CN104963731B/en not_active Expired - Fee Related
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| Publication number | Publication date |
|---|---|
| CN104963731A (en) | 2015-10-07 |
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| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20170201 Termination date: 20170421 |