CN205154271U - Aeroengine high pressure turbine cooling blast way arrangement structure - Google Patents
Aeroengine high pressure turbine cooling blast way arrangement structure Download PDFInfo
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- CN205154271U CN205154271U CN201520972993.9U CN201520972993U CN205154271U CN 205154271 U CN205154271 U CN 205154271U CN 201520972993 U CN201520972993 U CN 201520972993U CN 205154271 U CN205154271 U CN 205154271U
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Abstract
The utility model provides an aeroengine high pressure turbine cooling blast way arrangement structure, the back bleed pipe that includes a plurality of water conservancy diversion cooling gas of setting outside it cools off the leading trachea of gas and center on the second grade turbine casing to center on a plurality of water conservancy diversion that set up in the engine by -pass air duct outside the one -level turbine casing, the tracheal entrance point of leading is installed before the one -level turbine casing in the mount pad mounting hole, and the exit end is installed behind one -level machine casket in the mounting hole of installation limit, the gas collecting chamber intercommunication of the import of leading trachea and one -level nozzle ring, after draw tracheal exit end and install behind the second grade turbine casing in the mount pad mounting hole, the entrance point is installed before second grade machine casket in the mounting hole of installation limit draws the gas collecting chamber intercommunication of tracheal export and second grade nozzle ring after, import of back bleed pipe and leading air tube outlet set up the intercommunication relatively. The utility model discloses can simplify bleed mode and structure to reduce self temperature of cooling gas, thereby improve heat transfer and cooling efficiency.
Description
Technical field
The utility model relates to aero-turbine part of cooling system structure, is specifically related to a kind of layout of aeroengine high-pressure turbine cooling air stream.
Background technique
Aero-turbine cooling-part designs, under the prerequisite guaranteeing overall engine performance, the operating temperature of component should be reduced as far as possible, ensure that all parts all can at the allowable temperature operated within range of material, thus guarantee the validity of structure and function, the life-span meets design requirement.In addition, also to reduce the weight of component as far as possible, reduce aircraft own load.Certain model engine high pressure turbine is made up of first turbine and two-stage turbine, and the stator blade of first turbine and two-stage turbine all adopts hollow forced convection to cool, and its cooling air derives from the secondary gas flow having neither part nor lot in burning that high-pressure compressor provides.Secondary gas flow is guided to the air collecting chamber of two-stage turbine guider from the air collecting chamber of first turbine guider front end, be injected in the hollow blade of two-stage turbine guider after gas blending evenly, thus realize the cooling to two-stage turbine stator blade.The bleed mode of secondary gas flow routine, is the annular space of double-layered case by first turbine and two-stage turbine double-layered case, secondary gas flow is guided to the air collecting chamber of two-stage turbine guider from the air collecting chamber of first turbine guider front end.Conventional is this by double-layered case annular space bleed mode, and its gas circuit structure exists significantly not enough: 1 double layer construction casing, and case structure is complicated and weight is larger; 2, linkage structure is more, and outer casing mostly is sheet metal component, and machining deformation is large, and assembling is complicated; Although 3, secondary gas flow can carry out heat exchange by outer casing and by-pass air duct, simultaneously also from internal layer casing Surface absorption heat, therefore cooling blast cooling-down effect is low.
Summary of the invention
For the deficiency of existing structure, the purpose of this utility model aims to provide a kind of new aeroengine high-pressure turbine cooling air stream layout, to simplify the structure of component and to reduce own wt, reduces the own temperature of cooled gas, improves cooling effectiveness.
Based on foregoing invention object, the utility model provides aeroengine high-pressure turbine cooling air stream layout, it forms the rear air entraining pipe be included in around the some front air entraining pipes of water conservancy diversion cooling air of first turbine casing arranged outside and the some water conservancy diversion cooling air around two-stage turbine casing arranged outside in motor by-pass air duct, the entrance point of described front air entraining pipe to be arranged on before first turbine casing in fitting seat mounting hole, outlet end is arranged on after first turbine casing in mounting edge mounting hole, and front air entraining pipe import is communicated with the air collecting chamber of first turbine guider; The outlet end of described rear air entraining pipe to be arranged on after two-stage turbine casing in fitting seat mounting hole, entrance point to be arranged on before two-stage turbine casing in mounting edge mounting hole, the outlet of rear air entraining pipe is communicated with the air collecting chamber of two-stage turbine guider, and rear air entraining pipe import exports to be oppositely arranged with front air entraining pipe and is communicated with.
In technique scheme of the present utility model, described front air entraining pipe is preferably evenly arranged in motor by-pass air duct relative to unsettled outside first turbine casing, makes front air entraining pipe be placed in cryogenic gas in by-pass air duct completely, is conducive to heat exchange.
In technique scheme of the present utility model, the front fitting seat circumference outer rim decision design on first turbine casing is convex-concave plum blossom structure, and arrange mounting hole in flange portion, recessed edge is divided and is conducive to alleviator weight.
In technique scheme of the present utility model, the front fitting seat mounting hole on first turbine casing is designed with the seam for air entraining pipe before axially locating, avoids using screw-nut to fix, and is conducive to alleviator weight.
In technique scheme of the present utility model, one end that front air entraining pipe matches with front fitting seat mounting hole is straight pipe wall end, the one end of matching with rear mounting edge mounting hole is flared end, and enlarging diameter is greater than mounting hole internal diameter, is conducive to docking with the rear bleed mouth of pipe.
In technique scheme of the present utility model, the pipe thickness preferentially front air entraining pipe being designed to its two mounting end is greater than the pipe thickness of intermediate body portion, has both been conducive to intermediate host tubular portion and has carried out heat exchange, and can reduce again the weight of front air entraining pipe.
In technique scheme of the present utility model, described rear air entraining pipe is preferably evenly arranged in motor by-pass air duct relative to unsettled outside two-stage turbine casing, makes rear air entraining pipe be placed in cryogenic gas in by-pass air duct completely, is conducive to heat exchange.
In technique scheme of the present utility model, the rear fitting seat circumference outer rim decision design on two-stage turbine casing is convex-concave plum blossom structure, and flange is used for arranging mounting hole, and recessed edge is conducive to alleviator weight.
In technique scheme of the present utility model, the rear fitting seat mounting hole on two-stage turbine casing is designed with the seam for air entraining pipe after axially locating, avoids using screw-nut to fix, and is conducive to alleviator weight.
In technique scheme of the present utility model, the pipe thickness preferentially rear air entraining pipe being designed to its two mounting end is greater than the pipe thickness of intermediate body portion, has both been conducive to intermediate host tubular portion and has carried out heat exchange, and can reduce again the weight of front air entraining pipe.
In said method of the present utility model, the quantity of forward and backward air entraining pipe, caliber and circumferential distribution angle and its placing height relative to casing can be selected arbitrarily according to demand.
Compared with prior art, the utility model has following beneficial effect:
1, aeroengine high-pressure turbine cooling air stream layout described in the utility model, the many unsettled air entraining pipes be evenly arranged in by-pass air duct are adopted to carry out water conservancy diversion cooled gas, double-layered case bleed structure compared to existing technology, the unsettled cryogenic gas being arranged in by-pass air duct of bleed pipeline, the pipeline of the certain stroke of airflow passes, owing to there is the larger temperature difference inside and outside bleed pipeline, automatically convection heat exchange is produced by tube wall, in pipe, gas heat is taken away by by-pass air duct gas, temperature reduces, heat exchange efficiency improves greatly, when gas after cooling participates in cooling below, effectively can improve cooling effectiveness.
2, aeroengine high-pressure turbine cooling air stream layout described in the utility model, adopt pipeline bleed, the tube wall volume of air entraining pipe is far smaller than the volume of the outer casing of double-layered case, the intermediate host pipe thickness of air entraining pipe is little compared with mounting end thickness, fitting seat circumference outer rim is convex-concave plum blossom structure, and these structures are all conducive to alleviating total weight; And whole installation does not use any screw bolt and nut etc. to fix, and is directly located by seam, the mutual axial compression of casing end face.Compare traditional double-layered case double wall cavate flow guide structure and there is lightweight, that structure is simple, reliable and stable advantage.
3, aeroengine high-pressure turbine cooling air stream layout described in the utility model effectively limits cooled gas flow by designing different pipeline diameters, conveniently can control cold air flow without the need to special metering hole.
Accompanying drawing explanation
Fig. 1 is the schematic diagram of aeroengine high-pressure turbine cooling air stream layout described in the utility model.
Fig. 2 is the schematic diagram of the front fitting seat on first turbine casing.
Fig. 3 be in Fig. 2 A-A to sectional view.
Fig. 4 is the schematic diagram of the rear fitting seat on two-stage turbine casing.
Fig. 5 be in Fig. 4 B-B to schematic diagram.
Fig. 6 is the sectional drawing of front air entraining pipe.
Fig. 7 is the sectional drawing of rear air entraining pipe.
In figure, 1-front fitting seat, 2-rear fitting seat, 3-front air entraining pipe, 4-rear air entraining pipe, 5-rear mounting hole, the air collecting chamber of 6-first turbine guider, the air collecting chamber of 7-two-stage turbine guider, 8-front mounting hole, 9-first turbine casing, 10-two-stage turbine casing, 11-by-pass air duct, mounting edge after 12-one-level casing, mounting edge before 13-secondary casing.
Embodiment
Embodiment of the present utility model is provided below in conjunction with accompanying drawing; and by embodiment, the utility model is specifically described; what be necessary to herein means out is; embodiment is only for being further described the utility model; the restriction to the utility model protection domain can not be interpreted as; person skilled in art can make some nonessential improvement according to content of the present utility model and adjustment is specifically implemented, but so concrete enforcement should still belong to protection domain of the present utility model.
Embodiment 1
Aeroengine high-pressure turbine cooling air stream layout, due in motor by-pass air duct 11 around 12 front air entraining pipes of water conservancy diversion cooling air 3 of first turbine casing arranged outside with form around the rear air entraining pipe 4 of 12 water conservancy diversion cooling air of two-stage turbine casing arranged outside, the entrance point of described front air entraining pipe to be arranged on before first turbine casing in fitting seat 1 mounting hole 8, outlet end is arranged on after one-level casing in mounting edge 12 mounting hole, and front air entraining pipe import is communicated with the air collecting chamber 6 of first turbine guider; The outlet end of described rear air entraining pipe to be arranged on after two-stage turbine casing in fitting seat 2 mounting hole 5, entrance point is arranged on and is positioned at mounting edge 13 mounting hole before secondary casing, the outlet of rear air entraining pipe is communicated with the air collecting chamber 7 of two-stage turbine guider, and rear air entraining pipe import exports to be oppositely arranged with front air entraining pipe and is communicated with.Described front air entraining pipe is evenly arranged in motor by-pass air duct relative to unsettled outside first turbine casing, one end that front air entraining pipe matches with front fitting seat mounting hole is straight pipe wall end, the one end of matching with rear mounting edge mounting hole is flared end, enlarging diameter is greater than mounting hole internal diameter, is conducive to docking with the rear bleed mouth of pipe.Rear air entraining pipe is evenly arranged in motor by-pass air duct relative to unsettled outside two-stage turbine casing.The pipe thickness of forward and backward air entraining pipe two mounting end is greater than intermediate host pipe thickness.Forward and backward fitting seat mounting hole is all designed with the seam for air entraining pipe before and after axially locating.Forward and backward fitting seat circumference outer rim is convex-concave plum blossom structure, is conducive to alleviating structure weight.
Claims (10)
1. an aeroengine high-pressure turbine cooling air stream layout, it is characterized in that, be included in motor by-pass air duct (11) around the some front air entraining pipes of water conservancy diversion cooling air (3) of first turbine casing arranged outside and the rear air entraining pipe (4) around some water conservancy diversion cooling air of two-stage turbine casing arranged outside, the entrance point of described front air entraining pipe to be arranged on before first turbine casing in fitting seat (1) mounting hole (8), outlet end to be arranged on after first turbine casing in mounting edge (12) mounting hole, front air entraining pipe import is communicated with the air collecting chamber (6) of first turbine guider, the outlet end of described rear air entraining pipe to be arranged on after two-stage turbine casing in fitting seat (2) mounting hole (5), entrance point to be arranged on before two-stage turbine casing in mounting edge (13) mounting hole, the outlet of rear air entraining pipe is communicated with the air collecting chamber (7) of two-stage turbine guider, and rear air entraining pipe import exports to be oppositely arranged with front air entraining pipe and is communicated with.
2. aeroengine high-pressure turbine cooling air stream layout according to claim 1, it is characterized in that, described front air entraining pipe is evenly arranged in motor by-pass air duct relative to unsettled outside first turbine casing.
3. aeroengine high-pressure turbine cooling air stream layout according to claim 2, is characterized in that, the front fitting seat circumference outer rim on first turbine casing is convex-concave plum blossom structure.
4. aeroengine high-pressure turbine cooling air stream layout according to claim 3, it is characterized in that, the front fitting seat mounting hole on first turbine casing is designed with the seam for air entraining pipe before axially locating.
5. aeroengine high-pressure turbine cooling air stream layout according to claim 4, it is characterized in that, one end that front air entraining pipe matches with front fitting seat mounting hole is straight pipe wall end, and the one end of matching with rear mounting edge mounting hole is flared end, and enlarging diameter is greater than this mounting hole internal diameter.
6. aeroengine high-pressure turbine cooling air stream layout according to claim 5, it is characterized in that, the pipe thickness of front air entraining pipe two mounting end is greater than intermediate host pipe thickness.
7. the aeroengine high-pressure turbine cooling air stream layout according to any one of claim 1 to 6, it is characterized in that, described rear air entraining pipe is evenly arranged in motor by-pass air duct relative to unsettled outside two-stage turbine casing.
8. aeroengine high-pressure turbine cooling air stream layout according to claim 7, is characterized in that, the rear fitting seat circumference outer rim on two-stage turbine casing is convex-concave plum blossom structure.
9. aeroengine high-pressure turbine cooling air stream layout according to claim 8, it is characterized in that, the rear fitting seat mounting hole on two-stage turbine casing is designed with the seam for air entraining pipe after axially locating.
10. aeroengine high-pressure turbine cooling air stream layout according to claim 9, it is characterized in that, the pipe thickness of rear air entraining pipe two mounting end is greater than intermediate host pipe thickness.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520972993.9U CN205154271U (en) | 2015-11-30 | 2015-11-30 | Aeroengine high pressure turbine cooling blast way arrangement structure |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520972993.9U CN205154271U (en) | 2015-11-30 | 2015-11-30 | Aeroengine high pressure turbine cooling blast way arrangement structure |
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| CN205154271U true CN205154271U (en) | 2016-04-13 |
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| CN201520972993.9U Active CN205154271U (en) | 2015-11-30 | 2015-11-30 | Aeroengine high pressure turbine cooling blast way arrangement structure |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105401986A (en) * | 2015-11-30 | 2016-03-16 | 成都发动机（集团）有限公司 | Flow channel arrangement structure of aero-engine high-pressure turbine cooling air |
| JP6961856B1 (en) * | 2021-06-16 | 2021-11-05 | 三菱パワー株式会社 | Turbine assembly and how to assemble the turbine assembly |
-
2015
- 2015-11-30 CN CN201520972993.9U patent/CN205154271U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105401986A (en) * | 2015-11-30 | 2016-03-16 | 成都发动机（集团）有限公司 | Flow channel arrangement structure of aero-engine high-pressure turbine cooling air |
| JP6961856B1 (en) * | 2021-06-16 | 2021-11-05 | 三菱パワー株式会社 | Turbine assembly and how to assemble the turbine assembly |
| WO2022264865A1 (en) * | 2021-06-16 | 2022-12-22 | 三菱重工業株式会社 | Turbine assembly and method for assembling turbine assembly |
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