CN107218083A - A kind of curved hole preswirl nozzle for structure of being prewhirled for cold air - Google Patents
A kind of curved hole preswirl nozzle for structure of being prewhirled for cold air Download PDFInfo
- Publication number
- CN107218083A CN107218083A CN201710474463.5A CN201710474463A CN107218083A CN 107218083 A CN107218083 A CN 107218083A CN 201710474463 A CN201710474463 A CN 201710474463A CN 107218083 A CN107218083 A CN 107218083A
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- nozzle
- curved hole
- air
- deflection
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- 230000007704 transition Effects 0.000 claims abstract description 4
- 238000011144 upstream manufacturing Methods 0.000 claims description 7
- 238000001816 cooling Methods 0.000 abstract description 4
- 230000000694 effects Effects 0.000 abstract description 4
- 238000012913 prioritisation Methods 0.000 description 3
- 230000001133 acceleration Effects 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000008676 import Effects 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000012545 processing Methods 0.000 description 2
- 238000000926 separation method Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008901 benefit Effects 0.000 description 1
- 239000000112 cooling gas Substances 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
Abstract
The invention discloses a kind of curved hole preswirl nozzle for structure of being prewhirled for cold air, the entrance straight section being sequentially connected, changeover portion and deflection section are included；Axis of the axis of changeover portion respectively with the deflection axis of section, entrance straight section is tangent；Entrance straight section, changeover portion are identical with the cross-sectional area of deflection section, and air-flow first passes through entrance straight section and then sprayed by changeover portion, finally from deflection section；Changeover portion axis radius is more than the radius of curved hole preswirl nozzle.The present invention is widely used in high-temperature component of gas turbine cooling system, air-flow can effectively reduce air flow inlet loss when entering entrance straight section, when air-flow enters deflection section by entrance straight section, there is a smooth arc transition section centre, air-flow can be effectively reduced and enter the pressure loss produced during deflection section, final increase air-flow improves discharge coefficient by speed during nozzle, reaches that raising is prewhirled the purpose of cooling effect.
Description
Technical field
The present invention relates to the systems technology field of prewhirling in aero-engine air system, it is related to one kind and is prewhirled for cold air
The curved hole preswirl nozzle of structure.
Background technology
The raising of aeroengine thrust depends on the raising of turbine entrance temperature temperature, but the rising of fuel gas temperature
The working environment of the high-temperature components such as engine turbine blade is drastically deteriorated, thus influence turbo blade life-span and work can
By property.Prewhirl important component of the cooling system as engine air supply systems, its effect is carried for engine turbine blade
Cooling gas for unfavourable pressure, temperature is cooled down to turbo blade, so as to extend the service life and reliability of blade.
The principle of cooling of prewhirling is that airflow through preswirl nozzle expansion acceleration, produces and turbine disk direction of rotation identical week
To component velocity, reduction air-flow static temperature and the relative velocity with rotating disk, so as to reduce the relatively total relative to the turbine disk of air-flow
Temperature.There are some researches show the quality of preswirl nozzle design directly affects temperature drop effect of prewhirling.
The early stage nozzle of researcher's design both at home and abroad is mainly straight circular hole nozzle, and straight circular hole nozzle can be produced in porch
Raw larger flow separation, the flow losses of air-flow are big, and acceleration is poor, and discharge coefficient is low.To improve the property of straight circular hole nozzle
Can, nozzle entrance is carried out rounding processing to mitigate the flow losses of nozzle entrance by researcher；Later researcher will be straight
The inlet area increase of circular hole nozzle, devises a kind of pneumatic hole-shaped nozzle, this nozzle can reduce air-flow in nozzle entrance
The flow velocity at place, greatly reduces the flow losses of nozzle, improves discharge coefficient.Because pneumatic pass nozzle entrance area compares exit face
Product is big, and circumferentially number is restricted by inlet area.To improve the performance of preswirl nozzle to greatest extent, researcher sets
Cascade-type nozzle is counted out, this nozzle includes pressure face and suction surface, and nozzle entrance area is more than the area of jet expansion, tool
There is good aeroperformance, but the processing of cascade-type nozzle and installation difficulty are larger.
The content of the invention
The technical problems to be solved by the invention are to be directed to defect involved in background technology there is provided one kind for cold
Gas is prewhirled the curved hole preswirl nozzle of structure.
The present invention uses following technical scheme to solve above-mentioned technical problem：
A kind of curved hole preswirl nozzle for structure of being prewhirled for cold air, includes the entrance straight section being sequentially connected, changeover portion and deflection section；
The entrance straight section, deflection section are straight line hollow pipe, and changeover portion is circular arc hollow pipe, and the axis point of changeover portion
The axis of axis, entrance straight section not with deflection section is tangent；
The entrance straight section, changeover portion are identical with the cross-sectional area of deflection section, and air-flow first passes through entrance straight section and then by transition
Section, last sprayed from deflection section；
The changeover portion axis radius is more than the radius of curved hole preswirl nozzle.
It is described as a kind of curved further prioritization scheme of hole pass preswirl nozzle for structure of being prewhirled for cold air of the present invention
The axis of entrance straight section is vertical with the upstream card of curved hole preswirl nozzle, the angle of deflection section and curved hole preswirl nozzle downstream card
Scope be 15 degree to 90 degree.
It is described as a kind of curved further prioritization scheme of hole pass preswirl nozzle for structure of being prewhirled for cold air of the present invention
The length for deflecting section is more than or equal to 2 times of curved hole preswirl nozzle diameter.
It is described as a kind of curved further prioritization scheme of hole pass preswirl nozzle for structure of being prewhirled for cold air of the present invention
Entrance straight section does chamfered with nozzle upstream card, to reduce air-flow into loss during curved hole preswirl nozzle.
The present invention uses above technical scheme compared with prior art, with following technique effect：
Curved hole preswirl nozzle proposed by the present invention for system of prewhirling, compares with straight circular hole nozzle, can reduce air-flow in nozzle
The deflection loss of porch and flow separation loss, increase nozzle discharge velocity, improve the discharge coefficient and temperature of prewhirling of nozzle
Drop.Compared with pneumatic hole-shaped nozzle with cascade-type nozzle, because nozzle entrance area is less than exit area of nozzle, the circumference of nozzle
Arrangement number is improved.
Brief description of the drawings
Fig. 1 is the structural representation of curved hole preswirl nozzle of the invention；
Fig. 2 is the sectional view of curved hole preswirl nozzle of the invention；
Fig. 3 is the import cross section profile figure of curved hole preswirl nozzle of the invention；
Fig. 4 is the outlet profile diagram of curved hole preswirl nozzle of the invention.
In figure, 1- nozzle entrance straight sections, 2- nozzle changeover portions, 3- nozzles deflection section, 4- nozzle upstream cards, 5- nozzles enter
Mouth cross section profile, 6- nozzles downstream card, 7- jet expansion profiles.
Embodiment
Technical scheme is described in further detail below in conjunction with the accompanying drawings：
As depicted in figs. 1 and 2, present embodiment discloses a kind of curved hole preswirl nozzle in system of prewhirling, including entrance are straight
Section, changeover portion and deflection section.
Nozzle structural parameters in the present embodiment：L1- length at entry, L2- transition section length, L3- deflection segment length, R- mistakes
Cross a section axis radius, D- nozzle diameters,θ- pre-swirl angle.
Entrance straight section, deflection section are straight line hollow pipe, and changeover portion is circular arc hollow pipe, the axis of entrance straight section with
Curved hole preswirl nozzle upstream card is vertical, the axis of changeover portion axis respectively with deflection section, entrance straight section axis it is tangent, partially
Turn the angle of section and curved hole preswirl nozzle downstream cardθFor pre-swirl angle, angular region of prewhirling is 15 degree to 90 degree.
Perpendicular to axis direction, entrance straight section, changeover portion, the section for deflecting section are rounded, and area is identical, i.e., entirely
The diameter of curved each section of hole preswirl nozzle is identical.
In order to ensure that nozzle has good deflection characteristic to air-flow, the length of deflection section is more than or equal to curved hole preswirl nozzle
2 times of diameter.
Changeover portion axis radius R have to be larger than the radius of curved hole preswirl nozzle.
It is understood that the entrance straight section and nozzle upstream card do chamfered, it the advantage is that, air-flow can be with
Swimmingly enter curved hole preswirl nozzle, reduce loss when air-flow enters curved hole preswirl nozzle.
In the present embodiment, it is ensured that in the case of nozzle radial position, total length and spout radius identical, curved hole is contrasted pre-
The performance difference of churning mouth and straight circular hole preswirl nozzle：
Nozzle total circulation area A=706.86mm2, nozzle diameter D=5mm, radial position 130mm, number of nozzle is N=36, in advance
Swing angle degree isθ=30 °, changeover portion radius is 10mm, and nozzle entrance straight section length 3.84mm, deflection segment length is 15mm, nozzle
Total length 30mm.
The discharge coefficient of two kinds of nozzles when following table is the pressure ratio 1.5 obtained by CFD numerical simulations.Can from table
Go out, the discharge coefficient of curved hole preswirl nozzle of the invention is higher by 8.1% than straight circular hole nozzle, it can be seen that curved hole of the invention
Preswirl nozzle can reduce nozzle interior air-flow flow losses, increase nozzle outlet speed, so as to improve the discharge coefficient of nozzle.
| Discharge coefficient | |
| Straight circular hole preswirl nozzle | 0.719 |
| Curved hole preswirl nozzle | 0.778 |
Fig. 3, Fig. 4 are the import cross section profile figure and outlet profile diagram of curved hole preswirl nozzle of the invention respectively.
Those skilled in the art of the present technique are it is understood that unless otherwise defined, all terms used herein（Including skill
Art term and scientific terminology）With the general understanding identical meaning with the those of ordinary skill in art of the present invention.Also
It should be understood that those terms defined in such as general dictionary should be understood that with the context of prior art
The consistent meaning of meaning, and unless defined as here, will not be explained with idealization or excessively formal implication.
Above-described embodiment, has been carried out further to the purpose of the present invention, technical scheme and beneficial effect
Describe in detail, should be understood that the embodiment that the foregoing is only the present invention, be not limited to this hair
Bright, within the spirit and principles of the invention, any modification, equivalent substitution and improvements done etc. should be included in the present invention
Protection domain within.
Claims (4)
1. a kind of curved hole preswirl nozzle for structure of being prewhirled for cold air, it is characterised in that include the entrance straight section, mistake being sequentially connected
Cross section and deflection section；
The entrance straight section, deflection section are straight line hollow pipe, and changeover portion is circular arc hollow pipe, and the axis point of changeover portion
The axis of axis, entrance straight section not with deflection section is tangent；
The entrance straight section, changeover portion are identical with the cross-sectional area of deflection section, and air-flow first passes through entrance straight section and then by transition
Section, last sprayed from deflection section；
The changeover portion axis radius is more than the radius of curved hole preswirl nozzle.
2. the curved hole pass preswirl nozzle for structure of being prewhirled as claimed in claim 1 for cold air, it is characterised in that the entrance
The axis of straight section is vertical with the upstream card of curved hole preswirl nozzle, deflection section and the model of the angle of curved hole preswirl nozzle downstream card
Enclose for 15 degree to 90 degree.
3. the curved hole preswirl nozzle for structure of being prewhirled as claimed in claim 1 for cold air, it is characterised in that the deflection section
Length is more than or equal to 2 times of curved hole preswirl nozzle diameter.
4. the curved hole preswirl nozzle for structure of being prewhirled as claimed in claim 1 for cold air, it is characterised in that the entrance straight section
Chamfered is done with nozzle upstream card, to reduce air-flow into loss during curved hole preswirl nozzle.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710474463.5A CN107218083A (en) | 2017-06-21 | 2017-06-21 | A kind of curved hole preswirl nozzle for structure of being prewhirled for cold air |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710474463.5A CN107218083A (en) | 2017-06-21 | 2017-06-21 | A kind of curved hole preswirl nozzle for structure of being prewhirled for cold air |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107218083A true CN107218083A (en) | 2017-09-29 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710474463.5A Pending CN107218083A (en) | 2017-06-21 | 2017-06-21 | A kind of curved hole preswirl nozzle for structure of being prewhirled for cold air |
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| Country | Link |
|---|---|
| CN (1) | CN107218083A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112196628A (en) * | 2020-09-25 | 2021-01-08 | 中国航发沈阳发动机研究所 | Low-pressure turbine air cooling blade |
| CN112324522A (en) * | 2020-11-03 | 2021-02-05 | 中国民航大学 | Swirl effect-based prewhirl nozzle |
| 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 |
| CN113252290A (en) * | 2021-04-22 | 2021-08-13 | 哈尔滨工业大学 | Mars low-pressure supersonic ejector with ultralow-pressure input and high-wind-speed output |
| US11613996B2 (en) | 2019-11-28 | 2023-03-28 | Rolls-Royce Deutschland Ltd & Co Kg | Pre-swirl nozzle carrier and method of manufacturing the same |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5197509A (en) * | 1990-06-06 | 1993-03-30 | Cheng Dah Y | Laminar flow elbow system and method |
| US5529084A (en) * | 1994-03-24 | 1996-06-25 | Koch Engineering Company, Inc. | Laminar flow elbow system and method |
| CN103867235A (en) * | 2012-12-18 | 2014-06-18 | 中航商用航空发动机有限责任公司 | Tubular vortex reducer air inducing system |
| US20170030210A1 (en) * | 2015-07-28 | 2017-02-02 | Rolls-Royce Deutschland Ltd & Co Kg | Nozzle guide vane and method for forming such nozzle guide vane |
| CN206972310U (en) * | 2017-06-21 | 2018-02-06 | 南京航空航天大学 | A kind of curved hole preswirl nozzle for structure of being prewhirled for cold air |
-
2017
- 2017-06-21 CN CN201710474463.5A patent/CN107218083A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5197509A (en) * | 1990-06-06 | 1993-03-30 | Cheng Dah Y | Laminar flow elbow system and method |
| US5529084A (en) * | 1994-03-24 | 1996-06-25 | Koch Engineering Company, Inc. | Laminar flow elbow system and method |
| CN103867235A (en) * | 2012-12-18 | 2014-06-18 | 中航商用航空发动机有限责任公司 | Tubular vortex reducer air inducing system |
| US20170030210A1 (en) * | 2015-07-28 | 2017-02-02 | Rolls-Royce Deutschland Ltd & Co Kg | Nozzle guide vane and method for forming such nozzle guide vane |
| CN206972310U (en) * | 2017-06-21 | 2018-02-06 | 南京航空航天大学 | A kind of curved hole preswirl nozzle for structure of being prewhirled for cold air |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US11613996B2 (en) | 2019-11-28 | 2023-03-28 | Rolls-Royce Deutschland Ltd & Co Kg | Pre-swirl nozzle carrier and method of manufacturing the same |
| CN112196628A (en) * | 2020-09-25 | 2021-01-08 | 中国航发沈阳发动机研究所 | Low-pressure turbine air cooling blade |
| CN112196628B (en) * | 2020-09-25 | 2022-06-07 | 中国航发沈阳发动机研究所 | Low-pressure turbine air cooling blade |
| CN112324522A (en) * | 2020-11-03 | 2021-02-05 | 中国民航大学 | Swirl effect-based prewhirl nozzle |
| 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 |
| CN113252290A (en) * | 2021-04-22 | 2021-08-13 | 哈尔滨工业大学 | Mars low-pressure supersonic ejector with ultralow-pressure input and high-wind-speed output |
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Application publication date: 20170929 |