CN207960689U - One kind is for the radial azimuthal nozzle arrangements of system band of prewhirling - Google Patents
One kind is for the radial azimuthal nozzle arrangements of system band of prewhirling Download PDFInfo
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- CN207960689U CN207960689U CN201820050902.XU CN201820050902U CN207960689U CN 207960689 U CN207960689 U CN 207960689U CN 201820050902 U CN201820050902 U CN 201820050902U CN 207960689 U CN207960689 U CN 207960689U
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Abstract
The utility model discloses one kind for the radial azimuthal nozzle arrangements of system band of prewhirling, it is a kind of aero-engine and ground gas turbine is radially prewhirled in system with azimuthal nozzle arrangements, the azimuth of nozzle is by two angle controls of θ and α, wherein θ is the pre-swirl angle of nozzle, and α is nozzle-axis in axial drift angle.The utility model is widely used in high-temperature component of gas turbine cooling system, and advantage is：Reduce deflection angle of the air-flow in disk chamber, improve the circulation effect of air-flow, it can get the cold air flow of bigger under identical inlet and outlet pressure, and improve the cold air quality of turbo blade entrance, the temperature levels of the hot-end components such as the turbine disk and turbo blade have been effectively relieved.
Description
Technical field
The utility model is related to the diameters in rotating turbomachinery (aero-engine and ground gas turbine etc.) air system
To cooling technology field of prewhirling, it is related to a kind of prewhirling the azimuthal nozzle arrangements of system band for radial cold air.
Background technology
In recent years, with the continuous improvement of the loop parameters such as aero-engine thrust-weight ratio, ground gas turbine pressure ratio, especially
Be the increase of turbine entrance temperature temperature, the thermic load of the hot-end components such as the turbine disk, turbo blade caused to increased dramatically, the service life and
The reliability of trouble free service is seriously restricted, and to alleviate this problem, foreign study personnel propose the novel cold of air inlet of prewhirling
Gas intake method.Preswirl nozzle is the important component for the system of prewhirling, and effect is to provide cooling gas, is engine and combustion
The turbine disk and turbo blade of gas-turbine are cooled down, and for disk edge are obturaged equal positions and provided and obturage gas, to extend blade
Service life and reliability.
High pressure gas expands by preswirl nozzle and accelerates after compressor extraction, generates identical as turbine disk direction of rotation
Circumferential component velocity, reduce air-flow and turntable relative velocity, to reduce opposite total temperature of the air-flow relative to the turbine disk, reduction
The temperature of the turbine disk and turbo blade improves cooling effect.
Both at home and abroad to the preswirl nozzle in radial system of prewhirling studies have shown that with nozzle pre-swirl angle increase, temperature drop and
Pressure drop first reduces and increases afterwards therewith, and when pre-swirl angle is excessive, the extreme value place approximation of reduced performance of prewhirling, temperature drop and pressure drop is right
It answers, variation tendency almost synchronizes.Researcher has carried out various structures design to the nozzle of radial system of prewhirling at present, main to wrap
The nozzles such as straight pass, gradual shrinkage, cascade-type and pneumatic pass are included, high pressure gas accelerates by nozzle expansion, with perpendicular to rotation
The direction of axis is blown towards low radius, but this intake method haves the shortcomings that the pressure loss is larger, when air-flow is reached for conductance
The deflection close to 90 ° can occur when near flow table to adapt to runner variation, the cooling air-flow mobility of this process is poor, leads to whirlpool
The gas supply flow of the hot-end components such as impeller blade is insufficient, influences the stability of its service life and work.
Invention content
Goal of the invention：In order to overcome the deficiencies in the prior art, the utility model provide a kind of aero-engine and
Ground gas turbine is radially prewhirled in system with azimuthal nozzle arrangements, improves the cold air quality for air supply system of prewhirling, has
Effect alleviates the thermal stress of the hot-end components such as the turbine disk and turbo blade.
Technical solution：To achieve the above object, the technical solution adopted in the utility model is：Change radial preswirl nozzle
Arrangement form so that preswirl nozzle goes out component of the stream there are both direction, first, from high radius along perpendicular to the side of rotary shaft
To low radius is directed toward, have along the velocity component with rotary shaft parallel direction, the group of the two different angle second is that nozzle goes out stream
It closes and constitutes the different azimuth of nozzle.And then the circulation effect of air-flow can be improved, improve the flow for air supply system of prewhirling.
One kind being located at the annulus of quiet disk for the radial azimuthal nozzle arrangements of system band of prewhirling, the entrance of preswirl nozzle
On curved surface, and evenly distributed in the circumferential direction, the azimuth of preswirl nozzle by preswirl nozzle pre-swirl angle θ and preswirl nozzle axis
In axial two angle controls of drift angle α.
Further, where the outlet of preswirl nozzle on the section of circle ring surface, projection of the nozzle-axis on this face
It is known as nozzle in axial angle of deflection with the angle of traditional nozzle projection, α is 0 °~90 °.
Further, the angle between the section of circle ring surface where preswirl nozzle axis and jet expansion, perpendicular to
It is 10 °~90 ° that engine, which rotates the pre-swirl angle θ, θ that the projection angle on axial plane is nozzle,.
Further, the preswirl nozzle always points at the direction of turntable rotation.
Further, the structure of the nozzle is all including circular hole, cascade-type, gradual shrinkage and pneumatic pass
The nozzle arrangements of type.
Further, change the arrangement form of radial preswirl nozzle so that preswirl nozzle goes out point of the stream there are both direction
Amount, first, be directed toward low radius from high radius along perpendicular to the direction of rotary shaft, second is that nozzle go out stream have along with rotary shaft
The combination of the velocity component of parallel direction, the two different angle constitutes the different azimuth of nozzle.
Advantageous effect：It is provided by the utility model a kind of for the radial azimuthal nozzle arrangements of system band of prewhirling, and it is existing
There is technology to compare, has the advantage that：The utility model aero-engine and ground gas turbine are radially prewhirled band side in system
The nozzle arrangements of parallactic angle can reduce deflection angle of the air-flow in disk chamber, improve the circulation effect of air-flow, reduce gas supply of prewhirling
The pressure loss, can get the cold air flow of bigger under identical inlet and outlet pressure, and improve the cold air of turbo blade entrance
The temperature levels of the hot-end components such as the turbine disk and turbo blade have been effectively relieved in quality.
The utility model aero-engine and ground gas turbine are radially prewhirled in system with azimuthal nozzle arrangements, system
Position and the structure for not influencing other component when making mounting arrangements, do not influence the normal work of other structures.
Description of the drawings
Fig. 1 is the utility model band azimuth nozzle arrangements and radial system structure diagram of prewhirling.
Fig. 2 is the utility model band azimuth nozzle arrangements partial schematic diagram.
Fig. 3 is band azimuth nozzle arrangements sectional view.
Fig. 4 is band azimuth nozzle air inlet section radial direction schematic diagram.
In figure：
1. inlet chamber, 2. preswirl nozzles, 3. nozzle solid domains, 4. prewhirl chamber, 5. receiving orifices, and 6. prewhirl system outlet.
Specific implementation mode
The utility model discloses one kind for the radial azimuthal nozzle arrangements of system band of prewhirling, and is a kind of aeroplane engine
Machine and ground gas turbine are radially prewhirled in system with azimuthal nozzle arrangements, and the azimuth of nozzle is by two angle controls of θ and α
System, wherein θ are the pre-swirl angles of nozzle, and α is nozzle-axis in axial drift angle.The utility model is widely used in gas turbine height
In warm component cooling system, advantage is：Reduce deflection angle of the air-flow in chamber 4 of prewhirling, improves the circulation effect of air-flow
Fruit, can be by the cold air flow of 5 bigger of receiving orifice under identical inlet and outlet pressure, and improves cold at air supply outlet 6 of prewhirling
The temperature levels of the hot-end components such as the turbine disk and turbo blade have been effectively relieved in gas quality.
The utility model is further described with reference to the accompanying drawings and examples.
Embodiment
The present embodiment is that aero-engine and ground gas turbine are radially prewhirled in system with azimuthal nozzle arrangements, in advance
The azimuth of churning mouth 2 is by two angle controls of θ and α, and wherein θ is the pre-swirl angle of preswirl nozzle, and α is preswirl nozzle axis in axis
To drift angle, the above structure is described further below in conjunction with the accompanying drawings.
As shown in Figure 1, in radial system of prewhirling, high pressure cools down mainstream gas and reaches inlet chamber 1 after compressor extraction, with
Enter the expansion of preswirl nozzle 2 afterwards to accelerate, as shown in Fig. 2, 2 entrance of preswirl nozzle is located on the circle ring surface of quiet disk, and along circle
Circumferential direction is evenly arranged, the angle between the section of circle ring surface where preswirl nozzle axis and jet expansion, perpendicular to hair
Motivation rotates the pre-swirl angle θ that the projection angle on axial plane is nozzle, and ranging from 10 degree to 90 degree, preswirl nozzle always points at turntable
The direction of rotation, as shown in Figure 3.
When nozzle is there is only when angle, θ, referred to as traditional preswirl nozzle, the utility model band in system of radially prewhirling
Azimuthal nozzle arrangements are improved the air inlet angle of traditional preswirl nozzle, and improved preswirl nozzle not only has
Above-mentioned pre-swirl angle θ, also with nozzle in axial deflection angle α, as shown in figure 4, the circle ring surface where jet expansion is cut
On face, projection of the nozzle-axis on this face and the angle of traditional nozzle projection are known as nozzle in axial angle of deflection, model
Enclose is 0 degree to 90 degree.
The shape of nozzle solid domain 3, which can slightly be made, to be changed, to facilitate processing.
In system of radially prewhirling, the different combinations of preswirl nozzle θ angles and α angles, referred to as radial system of prewhirling
The azimuth of preswirl nozzle,
It is understood that nozzle can do chamfered with upstream, downstream disk, the advantage is that, air-flow can be smooth
Ground enters nozzle, reduces loss when air-flow enters nozzle.
The circular hole nozzle arrangements that Fig. 1 to Fig. 4 occurs are used merely to the azimuth feature of expression the utility model, this
The azimuth feature of utility model is suitable for all types of nozzles such as cascade-type, gradual shrinkage and pneumatic pass etc..
The above is only the preferred embodiment of the utility model, it should be pointed out that：For the common skill of the art
For art personnel, without departing from the principle of this utility model, several improvements and modifications can also be made, these improve and
Retouching also should be regarded as the scope of protection of the utility model.
Claims (6)
1. one kind is for the radial azimuthal nozzle arrangements of system band of prewhirling, it is characterised in that：The entrance of preswirl nozzle is located at
On the circle ring surface of quiet disk, and evenly distributed in the circumferential direction, the azimuth of preswirl nozzle is by the pre-swirl angle θ of preswirl nozzle and pre-
Nozzle-axis is revolved in axial two angle controls of drift angle α.
2. according to claim 1 for the radial azimuthal nozzle arrangements of system band of prewhirling, it is characterised in that：It is prewhirling
Where the outlet of nozzle on the section of circle ring surface, the angle that projection of the nozzle-axis on this face is projected with traditional nozzle claims
It is angle of deflection of the nozzle in axial direction, α is 0 °~90 °.
3. according to claim 1 for the radial azimuthal nozzle arrangements of system band of prewhirling, it is characterised in that：Pre- churning
Angle between the section of circle ring surface where mouth axis and jet expansion, in the projected angle on engine rotation axial plane
Degree is that the pre-swirl angle θ, θ of nozzle are 10 °~90 °.
4. according to claim 1 for the radial azimuthal nozzle arrangements of system band of prewhirling, it is characterised in that：It is described pre-
Churning mouth always points at the direction of turntable rotation.
5. according to claim 1 for the radial azimuthal nozzle arrangements of system band of prewhirling, it is characterised in that：The spray
The structure of mouth is all types of nozzle arrangements including circular hole, cascade-type, gradual shrinkage and pneumatic pass.
6. according to claim 1 for the radial azimuthal nozzle arrangements of system band of prewhirling, it is characterised in that：Change diameter
To the arrangement form of preswirl nozzle so that preswirl nozzle goes out component of the stream there are both direction, first, from high radius along vertical
It is directed toward low radius in the direction of rotary shaft, is had along the velocity component with rotary shaft parallel direction, the two second is that nozzle goes out stream
The combination of different angle constitutes the different azimuth of nozzle.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820050902.XU CN207960689U (en) | 2018-01-12 | 2018-01-12 | One kind is for the radial azimuthal nozzle arrangements of system band of prewhirling |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820050902.XU CN207960689U (en) | 2018-01-12 | 2018-01-12 | One kind is for the radial azimuthal nozzle arrangements of system band of prewhirling |
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| CN207960689U true CN207960689U (en) | 2018-10-12 |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108194147A (en) * | 2018-01-12 | 2018-06-22 | 南京航空航天大学 | One kind is for the azimuthal nozzle arrangements of system band of radially prewhirling |
| CN110552788A (en) * | 2019-09-19 | 2019-12-10 | 西北工业大学 | Cover plate disc with radial runway inclined hole type receiving hole for pre-rotation gas supply system |
| CN113123999A (en) * | 2021-03-26 | 2021-07-16 | 北京航空航天大学 | Shunting cooling type aero-engine compressor rear shaft diameter conical wall cavity |
-
2018
- 2018-01-12 CN CN201820050902.XU patent/CN207960689U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108194147A (en) * | 2018-01-12 | 2018-06-22 | 南京航空航天大学 | One kind is for the azimuthal nozzle arrangements of system band of radially prewhirling |
| CN110552788A (en) * | 2019-09-19 | 2019-12-10 | 西北工业大学 | Cover plate disc with radial runway inclined hole type receiving hole for pre-rotation gas supply system |
| CN113123999A (en) * | 2021-03-26 | 2021-07-16 | 北京航空航天大学 | Shunting cooling type aero-engine compressor rear shaft diameter conical wall cavity |
| CN113123999B (en) * | 2021-03-26 | 2022-01-28 | 北京航空航天大学 | Shunting cooling type aero-engine compressor rear shaft diameter conical wall cavity |
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