CN109751130A - A kind of cooling system of prewhirling of aero-engine - Google Patents
A kind of cooling system of prewhirling of aero-engine Download PDFInfo
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- CN109751130A CN109751130A CN201910032213.5A CN201910032213A CN109751130A CN 109751130 A CN109751130 A CN 109751130A CN 201910032213 A CN201910032213 A CN 201910032213A CN 109751130 A CN109751130 A CN 109751130A
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- nozzle
- prewhirling
- aero
- cooling system
- inlet
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- 238000001816 cooling Methods 0.000 title claims abstract description 56
- 238000005452 bending Methods 0.000 claims abstract description 4
- 230000000694 effects Effects 0.000 abstract description 6
- 238000010586 diagram Methods 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 2
- 230000005713 exacerbation Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000002269 spontaneous effect Effects 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
- 238000009423 ventilation Methods 0.000 description 1
Abstract
The present invention provides a kind of cooling systems of prewhirling of aero-engine, include the inlet chamber, prewhirl unit and outlet chamber of successively nested setting along gas travel path；Gas in inlet chamber is radially into unit of prewhirling, the unit of prewhirling includes the multiple nozzles being uniformly arranged in the circumferential direction, the nozzle with respect to inlet chamber radially bending be arranged, the nozzle from air inlet to gas outlet at least one section of runner along inlet chamber axial shrinkage；The outlet chamber is connected to cooling duct.Aero-engine provided by the invention prewhirl cooling system the advantages of be: increase nozzle air inlet area, convenient for airflow smooth enter nozzle in, reduce air-flow in the loss of inlet；Due to the presence of tapered runner, air velocity is improved, reduces power consumption, improves cooling effect, there is good promotion prospect.
Description
Technical field
The present invention relates to aero-engine secondary ventilation system cooling technology field more particularly to a kind of aero-engines
It prewhirls cooling system.
Background technique
In recent years, aero engine technology makes rapid progress, and engine performance has obtained biggish development.Improve engine
The main path of energy is to improve turbine inlet temperature and pressure ratio, but the raising of turbine inlet temperature makes the high temperature such as turbine in engine
The working environment severe exacerbation of component, so as to cause engine reliability variation, the lost of life.
Cooling system prewhirl as aero-engine air system important component, function is to guide cold air at rotation
Turn state to be transported in the cooling duct of the high-temperature components such as high-speed rotation turbo blade, reaching reduces mesh of the air-flow with respect to total temperature
, to improve cold air quality, enhance blade cooling effect, improves cooling efficiency.Cooling system in the prior art enters cold
But flow velocity when pipeline is lower, and jet expansion circumferential speed is smaller, causes system outlet eddy flow relatively low, cooling effect is bad.
Summary of the invention
Technical problem to be solved by the present invention lies in provide one kind to can be improved cold air flow velocity with jet expansion circumferential direction
Speed, thus the cooling system of prewhirling of lifting system discharge swirl ratio.
The present invention is to solve above-mentioned technical problem by the following technical programs:
A kind of cooling system of prewhirling of aero-engine, along gas travel path include successively the inlet chamber of nested setting,
It prewhirls unit and outlet chamber；For gas in inlet chamber radially into unit of prewhirling, the unit of prewhirling includes circumferentially uniform
The multiple nozzles being arranged, the nozzle with respect to inlet chamber radially bending be arranged, the nozzle from air inlet to gas outlet at least
There is one section of runner along inlet chamber axial shrinkage；The outlet chamber is connected to cooling duct.
Preferably, inlet chamber outer surface is evenly arranged with multiple radially secure air inlets, the nozzle and air inlet
It corresponds.
Preferably, the air inlet of the air inlet face nozzle.
Preferably, it is axially seen along inlet chamber, the air inlet from nozzle to gas outlet runner natural shrinking.
Preferably, it is axially seen along inlet chamber, the side of the nozzle face air inlet has the first rotating part, and described first
Outside the tangential direction runner of rotating part.
Preferably, the nozzle has tangential the second rotating part being directed toward inside runner backwards to the side of air inlet, described
The radius of gyration of the radius of gyration of first rotating part less than the second rotating part.
Preferably, the nozzle is respectively arranged with and the first rotating part and second close to the position of gas outlet along runner two sides
Rotating part is tangent and the straight panel that moves closer to, the runner that two straight panels surround gradually taper up.
Preferably, it is seen along the radial direction of inlet chamber, the two sides of the region runner of the preceding 1/2-2/3 of the nozzle are obliquely installed simultaneously
It moves closer to.
Preferably, the cooling duct is axial parallel with the tangential and inlet chamber of outlet chamber junction, the nozzle
Air-flow travel path inclination of the gas outlet into cooling duct.
Preferably, the air inlet and nozzle are respectively arranged with 15~25.
Aero-engine provided by the invention prewhirl cooling system the advantages of be: increase nozzle air inlet area, be convenient for
Entering in nozzle for airflow smooth, reduces air-flow in the loss of inlet；Due to the presence of tapered runner, gas velocity is improved
Degree reduces power consumption, improves cooling effect, has good promotion prospect.
Detailed description of the invention
Fig. 1 is the cooling system schematic diagram of prewhirling of aero-engine provided by the embodiment of the present invention；
Fig. 2 is the axial sectional view of the cooling system of prewhirling of aero-engine provided by the embodiment of the present invention；
Fig. 3 is the signal of the nozzle of the cooling system of prewhirling of aero-engine provided by the embodiment of the present invention radially
Figure；
Fig. 4 is prewhirl cooling system and the water conservancy diversion leaf in the prior art of nozzle arrangements provided by the embodiment of the present invention
The outlet circumferential speed comparison diagram of the cooling system of prewhirling of piece form；
Fig. 5 is prewhirl cooling system and the water conservancy diversion leaf in the prior art of nozzle arrangements provided by the embodiment of the present invention
The swirl ratio comparison diagram of the cooling system of prewhirling of piece form.
Specific embodiment
To make the objectives, technical solutions, and advantages of the present invention clearer, below in conjunction with specific embodiment, and reference
Attached drawing, the present invention is described in further detail.
As shown in Figure 1, a kind of cooling system of prewhirling of aero-engine, including along the successively nested setting of gas travel path
Inlet chamber 1, prewhirl unit 2 and outlet chamber 3, the gas of inlet chamber 1 is radially into unit 2 of prewhirling, the packet of unit 2 of prewhirling
The multiple nozzles 21 being uniformly arranged along axial direction are included, the radially bending of the opposite inlet chamber 1 of the nozzle 21 is arranged, the outlet chamber 3
It is connected to cooling duct (not shown), by the way that nozzle 21 is arranged to warp architecture, can make to enter the air prewhirled in unit 2
Outlet chamber 3 is rotated into, helically state is advanced in cooling duct to increase air-flow, improves air-flow in cooling duct
Time makes air-flow sufficiently exchange heat and cools down to aero-engine；The nozzle 21 is at least one section from air inlet to gas outlet
Runner improves air velocity, moves air-flow in cooling duct inside spin along 1 axial shrinkage of inlet chamber by shrinking runner
When generate biggish eccentric force, come into full contact with air-flow with cooling pipe, improve heat exchange efficiency.
The outer surface of the inlet chamber 1 is uniformly arranged in the circumferential direction multiple radially secure air inlets 11, the nozzle
21 correspond with air inlet 11, are provided with 15~25 air inlets 11 and nozzle 21 in preferred embodiment, mention in the present embodiment
The cooling system of prewhirling supplied is provided with 16 air inlets 11 and nozzle 21.The air inlet of 11 face nozzle 21 of air inlet, to drop
Low-flow enters energy loss when nozzle 21, obtains high-speed flow.
With reference to Fig. 2, the axial direction along inlet chamber 1 is seen, the air inlet of the nozzle 21 to gas outlet runner natural shrinking, thus
Further increase air velocity；The side of the 21 face air inlet 11 of nozzle have the first rotating part 22, nozzle 21 backwards into
The side of stomata 11 has the second rotating part 23, outside the tangential direction runner of first rotating part 22, the second rotating part 23
Tangential direction runner inside, and the radius of gyration of the first rotating part 22 is less than the radius of gyration of the second rotating part 23.Thus when
The runner that first rotating part 22 and the second rotating part 23 surround gradually tapers up.The nozzle 21 further include respectively with the first rotating part
22 and the tangent straight panel 24 in 23 end of the second rotating part, the runner that two straight panels 24 surround gradually taper up；The tail of the straight panel 24
End is connected to the surface of outlet chamber 3；To make air-flow is in a certain angle to enter outlet chamber 3, vortex gas is formed in outlet chamber 3
Stream.
With reference to Fig. 3, the radial direction along inlet chamber 1 is seen, the two sides inclination of the region runner of the money 1/2~2/3 of the nozzle 21
It is arranged and moves closer to, to forms the runner axially tapered along inlet chamber 1.Runner close to 21 tail end of nozzle can be set to
The structure constant along axial distance.
At work, cooling duct is traditionally arranged to be the axial direction for being parallel to outlet chamber 3 or cooling duct in junction
It is tangentially axial parallel with outlet chamber 3, it sets the end of nozzle 21 to being provided with the one of cooling duct in preferred embodiment
It rolls tiltedly, is that air-flow can be spontaneous along cooling logical to make the flow velocity of air-flow that there is the component in cooling duct direction of travel
Road advances, and without the promotion of air-flow below, reduces flow velocity loss when air-flow mutually impacts, improves cooling effect.
Fig. 4 and Fig. 5 is the effect contrast figure of prewhirl cooling system and the prior art provided in this embodiment, Ke Yiming respectively
It is aobvious to find out that the swirl ratio of the cooling system of prewhirling provided by the embodiment with nozzle arrangements is substantially better than the pre- of guide vane form
Whirl spraying mouth structure.
Claims (10)
1. a kind of cooling system of prewhirling of aero-engine, it is characterised in that: include successively nested setting along gas travel path
Inlet chamber, prewhirl unit and outlet chamber；For gas in inlet chamber radially into unit of prewhirling, the unit of prewhirling includes edge
The multiple nozzles being circumferentially uniformly arranged, radially bending of the nozzle with respect to inlet chamber are arranged, and the nozzle is from air inlet to out
Port at least one section of runner is along inlet chamber axial shrinkage；The outlet chamber is connected to cooling duct.
2. the cooling system of prewhirling of aero-engine according to claim 1, it is characterised in that: inlet chamber outer surface is uniform
Multiple radially secure air inlets are provided with, the nozzle and air inlet correspond.
3. a kind of cooling system of prewhirling of aero-engine according to claim 2, it is characterised in that: the air inlet is just
To the air inlet of nozzle.
4. a kind of cooling system of prewhirling of aero-engine according to claim 3, it is characterised in that: along inlet chamber axial direction
It sees, the air inlet from nozzle to gas outlet runner natural shrinking.
5. a kind of cooling system of prewhirling of aero-engine according to claim 4, it is characterised in that: along inlet chamber axial direction
It sees, the side of the nozzle face air inlet has the first rotating part, outside the tangential direction runner of first rotating part.
6. a kind of cooling system of prewhirling of aero-engine according to claim 5, it is characterised in that: the nozzle is backwards
The side of air inlet has tangential the second rotating part being directed toward inside runner, and the radius of gyration of first rotating part is less than second
The radius of gyration of rotating part.
7. a kind of cooling system of prewhirling of aero-engine according to claim 6, it is characterised in that: the nozzle is close
The position of gas outlet is respectively arranged with straight panel that is tangent with the first rotating part and the second rotating part and moving closer to along runner two sides,
The runner that two straight panels surround gradually tapers up.
8. a kind of cooling system of prewhirling of aero-engine according to claim 1, it is characterised in that: along the diameter of inlet chamber
To seeing, the two sides of the region runner of the preceding 1/2-2/3 of the nozzle are obliquely installed and move closer to.
9. a kind of cooling system of prewhirling of aero-engine according to claim 8, it is characterised in that: the cooling duct
Axial parallel with the tangential and inlet chamber of outlet chamber junction, air-flow of the gas outlet of the nozzle into cooling duct is advanced
Path inclination.
10. a kind of cooling system of prewhirling of aero-engine according to claim 2, it is characterised in that: the air inlet
15~25 are respectively arranged with nozzle.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910032213.5A CN109751130A (en) | 2019-01-14 | 2019-01-14 | A kind of cooling system of prewhirling of aero-engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910032213.5A CN109751130A (en) | 2019-01-14 | 2019-01-14 | A kind of cooling system of prewhirling of aero-engine |
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| Publication Number | Publication Date |
|---|---|
| CN109751130A true CN109751130A (en) | 2019-05-14 |
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ID=66405684
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910032213.5A Pending CN109751130A (en) | 2019-01-14 | 2019-01-14 | A kind of cooling system of prewhirling of aero-engine |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110370158A (en) * | 2019-08-20 | 2019-10-25 | 西北工业大学 | Abrasive Flow tooling applied to aero-engine preswirl nozzle surface of internal cavity finishing |
| CN112412544A (en) * | 2020-11-23 | 2021-02-26 | 东方电气集团东方汽轮机有限公司 | Gas turbine pneumatic hole type prerotation nozzle with inlet transition section |
| CN113123880A (en) * | 2021-03-26 | 2021-07-16 | 北京航空航天大学 | Low-entropy strong-production pre-rotation lap joint air entraining structure on static thin-walled part of aero-engine |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20020076318A1 (en) * | 2000-12-18 | 2002-06-20 | Kiritkumar Patel | Further cooling of pre-swirl flow entering cooled rotor aerofoils |
| CN105114186A (en) * | 2015-08-04 | 2015-12-02 | 西北工业大学 | Blade hole type prewhirl nozzle for prewhirl cooling system |
| CN105464724A (en) * | 2015-12-30 | 2016-04-06 | 中国航空工业集团公司沈阳发动机设计研究所 | Pneumatic hole type pre-swirl nozzle for pre-swirl cooling system |
| CN108071492A (en) * | 2017-12-19 | 2018-05-25 | 中国联合重型燃气轮机技术有限公司 | Gas turbine and its part flow arrangement of prewhirling |
| US20180223735A1 (en) * | 2017-02-07 | 2018-08-09 | Doosan Heavy Industries & Construction Co., Ltd. | Pre-swirler for gas turbine |
| CN209621472U (en) * | 2019-01-14 | 2019-11-12 | 南京航空航天大学 | A kind of cooling system of prewhirling of aero-engine |
-
2019
- 2019-01-14 CN CN201910032213.5A patent/CN109751130A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20020076318A1 (en) * | 2000-12-18 | 2002-06-20 | Kiritkumar Patel | Further cooling of pre-swirl flow entering cooled rotor aerofoils |
| CN105114186A (en) * | 2015-08-04 | 2015-12-02 | 西北工业大学 | Blade hole type prewhirl nozzle for prewhirl cooling system |
| CN105464724A (en) * | 2015-12-30 | 2016-04-06 | 中国航空工业集团公司沈阳发动机设计研究所 | Pneumatic hole type pre-swirl nozzle for pre-swirl cooling system |
| US20180223735A1 (en) * | 2017-02-07 | 2018-08-09 | Doosan Heavy Industries & Construction Co., Ltd. | Pre-swirler for gas turbine |
| CN108071492A (en) * | 2017-12-19 | 2018-05-25 | 中国联合重型燃气轮机技术有限公司 | Gas turbine and its part flow arrangement of prewhirling |
| CN209621472U (en) * | 2019-01-14 | 2019-11-12 | 南京航空航天大学 | A kind of cooling system of prewhirling of aero-engine |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110370158A (en) * | 2019-08-20 | 2019-10-25 | 西北工业大学 | Abrasive Flow tooling applied to aero-engine preswirl nozzle surface of internal cavity finishing |
| CN110370158B (en) * | 2019-08-20 | 2020-12-08 | 西北工业大学 | Abrasive flow tool applied to surface finishing of inner cavity of prewhirl nozzle of aircraft engine |
| CN112412544A (en) * | 2020-11-23 | 2021-02-26 | 东方电气集团东方汽轮机有限公司 | Gas turbine pneumatic hole type prerotation nozzle with inlet transition section |
| CN113123880A (en) * | 2021-03-26 | 2021-07-16 | 北京航空航天大学 | Low-entropy strong-production pre-rotation lap joint air entraining structure on static thin-walled part of aero-engine |
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