CN104963731A - Novel aero-engine thermal compensation structure - Google Patents
Novel aero-engine thermal compensation structure Download PDFInfo
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- CN104963731A CN104963731A CN201510191104.XA CN201510191104A CN104963731A CN 104963731 A CN104963731 A CN 104963731A CN 201510191104 A CN201510191104 A CN 201510191104A CN 104963731 A CN104963731 A CN 104963731A
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- thermal compensation
- holes
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- floor
- 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 aeroengine thermal compensation linkage structure, belong to aero propulsion technical field.
Background technique
Thermal compensation structure is the structure connecting rear housing and bearing support in some engine structure, and epimere is connected to support case, and lower end is connected with bearing support.Because intake temperature before turbine is very high, although rear housing can be cooled by structural design and cooling system, still extremely I haven't seen you for ages for temperature more than 500 DEG C, and bearing is due to lubrication restriction, its normal working temperature is generally no more than 300 DEG C, and both temperature difference are close to 200 DEG C.Therefore thermal compensation structure bears the mission of load and cooling simultaneously, enough intensity and appropriate rigidity should be had to support, realize cooling again at small space.
Thermal compensation structure will have on the one hand enough intensity and appropriate rigidity to ensure to support, and reduces heat transmission again on the other hand in comparatively short distance.
Summary of the invention
For the problems referred to above, the object of this invention is to provide a kind of aeroengine thermal compensation linkage structure, this structure, under the prerequisite not reducing thermal compensation linkage structure rigidity, can reduce the heat-conducting property of thermal compensation linkage structure obviously.
According to one embodiment of present invention, thermal compensation linkage structure adopts cross section to be the structural type of S, increases heat transfer distance, loop configuration is opened long oval pore, and object increases thermal-conduction resistance.In order to ensure rigidity requirement, add floor in S shape structure.
The profile of a kind of aeroengine thermal compensation linkage structure according to an embodiment of the invention is loop configuration, comprises mounting edge, lower mounting edge, floor, circular hole and long oval pore; It is characterized in that thermal compensation linkage structure has been opened long oval pore, added floor on the architecture basics of routine, its mesopore has two kinds of shapes, hole is long oval pore, be topmost between floor be also the hole that quantity is maximum, each row adopts cross one another mode to arrange with two rows, is cooling major measure, also has minority circular hole, mainly be distributed in floor both sides, the gap of each misarrangement perforate of cover.Floor one has 8, is distributed in loop configuration.
Beneficial effect of the present invention is: under the prerequisite meeting strength and stiffness designing requirement, can improve the thermal conduction effect of thermal compensation linkage structure by a relatively large margin.
Accompanying drawing explanation
Fig. 1 is the present invention: novel aeroengine thermal compensation linkage structure;
Fig. 2 is that aeroengine ordinary hot compensates linkage 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.
Number in the figure is described as follows:
1-upper mounting edge; 2-lower mounting edge; 3-floor; 4-circular port; Shape hole, the 5-long fourth of the twelve Earthly Branches.
Embodiment
The invention provides a kind of aeroengine thermal compensation linkage structure, below in conjunction with the drawings and specific embodiments, the present invention is further illustrated.
As shown in Figure 1, thermal compensation linkage structure according to an embodiment of the invention comprises: upper mounting edge 1, lower mounting edge 2, floor 3, circular port 4 and long oval pore 5 form.Upper mounting edge 1 is connected with rear housing, and lower mounting edge 2 is connected with bearing support, and because upper and lower temperature difference is comparatively large, main body employing cross section is the structural type of S shape, and object increases heat transfer distance.The annular region that agent structure has 3 parts to punch, the long oval pore of two rows or three rows is opened according to width size in each region, and each row staggers mutually with two rows, every array pitch is from remaining between 3mm ~ 5mm, distance is less, the heat transmitted is fewer, processing is got up also more difficult, distance between Kong Yukong remains on 2mm ~ 2.5mm, too little words intensity can not meet design requirement, too large words cooling-down effect is bad, close to floor 3 place due to long oval pore is staggered can not be completely the same, so there is no tapping making circular hole, this kind of structural design object farthest increases thermal-conduction resistance, lower the temperature to a greater degree.Meanwhile, in order to ensure the requirement of thermal compensation linkage structure strength and stiffness, add 8 floors 3 at S shape ring structure, alternate 45 ° of every bar floor 3, circumferentially arranges.Floor 3 is more wide thicker, and better for increase Rigidity and strength effect, thermal compensation linkage structure of the present invention only needs proof strength and rigidity Design to require.
The present inventor has carried out simulation analysis to the cooling-down effect of this thermal compensation linkage structure: apply initial temperature parameter in each face of thermal compensation linkage structure, carry out analysis of Heat Transfer, after drawing temperature field, applies axial constraint, carry out intensive analysis at lower mounting edge place.
Analysis of Heat Transfer result shows, and under this structure, mounting edge temperature (reading as 344.17 DEG C from Fig. 3) is well below the corresponding temperature (reading as 400 DEG C from Fig. 2) of original structure, and cooling-down effect is obvious.
Fig. 4 stress analysis result display maximum stress (496.36MPa) is distributed in floor bending part, because the original angle of S shape structure is just little, adds that floor is equivalent to increase thickness, angle is caused to reduce, so stress becomes large, bent angle can be increased by the mode of chamfering, reduce stress.Stress in addition between long oval pore increases along with the reduction of hole pitch, so little as best one can under the hole pitch prerequisite that will meet the demands at proof stress.
New structural type is introduced, perforate on the basis of agent structure, ribbed panel in the present invention.The object of perforate is the thermal-conduction resistance in order to increase structure, increases temperature drop.After perforate, the strength and stiffness of structure all decrease, and therefore increase floor and strength and stiffness are met design requirement.
Described structure has the following advantages: (1) can reduce the temperature of thermal compensation linkage structure lower end largely; (2) reduce weight and be conducive to overall engine design.
Claims (5)
1., for the thermal compensation connected element of the rear housing and bearing support that connect aeroengine, its feature comprises:
Upper mounting edge (1), for being connected with rear housing;
Lower mounting edge (2), for being connected with bearing support;
The main body of wherein said thermal compensation connected element has S tee section, has three annular regions, to increase heat transfer distance; Each described annular region has platoon leader's 2-3 oval pore.
2. thermal compensation connected element according to claim 1, is characterized in that comprising further:
Described S tee section is circumferentially provided with multiple floor (3), for ensureing the strength and stiffness of thermal compensation connected element.
3. thermal compensation connected element according to claim 2, is characterized in that:
Described floor (3) has eight, circumferentially equally spaced arranges.
4., according to the thermal compensation connected element of Claims 2 or 3, it is characterized in that:
The long oval pore of each row and the long oval pore of two rows stagger mutually, in the part of the described annular region close to floor (3), opening long oval pore place due to described floor (3), have circular port.
5. thermal compensation connected element according to claim 4, is characterized in that:
The distance of every platoon leader's oval pore/circular port is between 3mm-5mm, and the distance between the long oval pore/circular port of same row is at 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 true CN104963731A (en) | 2015-10-07 |
| CN104963731B CN104963731B (en) | 2017-02-01 |
Family
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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 |
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| CN (1) | CN104963731B (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3970164A (en) * | 1973-12-17 | 1976-07-20 | Yamaha Hatsudoki Kabushiki Kaisha | Small-sized snowmobile |
| US4622136A (en) * | 1985-08-23 | 1986-11-11 | Watson Karcey International | Reusable liquid filter assembly |
| US20050115700A1 (en) * | 2003-11-28 | 2005-06-02 | Michael Martin | Brazed sheets with aligned openings and heat exchanger formed therefrom |
| US20140060504A1 (en) * | 2012-09-06 | 2014-03-06 | Senior Ip Gmbh | Exhaust Gas Recirculation Apparatus and Method for Forming Same |
-
2015
- 2015-04-21 CN CN201510191104.XA patent/CN104963731B/en not_active Expired - Fee Related
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3970164A (en) * | 1973-12-17 | 1976-07-20 | Yamaha Hatsudoki Kabushiki Kaisha | Small-sized snowmobile |
| US4622136A (en) * | 1985-08-23 | 1986-11-11 | Watson Karcey International | Reusable liquid filter assembly |
| US20050115700A1 (en) * | 2003-11-28 | 2005-06-02 | Michael Martin | Brazed sheets with aligned openings and heat exchanger formed therefrom |
| US20140060504A1 (en) * | 2012-09-06 | 2014-03-06 | Senior Ip Gmbh | Exhaust Gas Recirculation Apparatus and Method for Forming Same |
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| Publication number | Publication date |
|---|---|
| CN104963731B (en) | 2017-02-01 |
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Granted publication date: 20170201 Termination date: 20170421 |
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| CF01 | Termination of patent right due to non-payment of annual fee |