CN112412544A - Gas turbine pneumatic hole type prerotation nozzle with inlet transition section - Google Patents
Gas turbine pneumatic hole type prerotation nozzle with inlet transition section Download PDFInfo
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- CN112412544A CN112412544A CN202011318439.0A CN202011318439A CN112412544A CN 112412544 A CN112412544 A CN 112412544A CN 202011318439 A CN202011318439 A CN 202011318439A CN 112412544 A CN112412544 A CN 112412544A
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- 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
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- 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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
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- General Engineering & Computer Science (AREA)
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Abstract
The invention relates to the technical field of gas turbines, and particularly discloses a gas turbine pneumatic hole type prewhirl nozzle with an inlet transition section, which comprises an inlet transition section and a nozzle section which are communicated in sequence; the axis of the inlet transition section intersects the axis of the nozzle section and forms an included angle a. The air flow does not need to deflect when entering the inlet transition section from the cavity in front of the inlet transition section, so that flow separation is reduced, and the flow is more uniform; meanwhile, the cross-sectional area of the inlet transition section, which is vertical to the axis, is larger than that of the nozzle section, which is vertical to the axis, so that the flow speed of the airflow in the inlet transition section is low; thereby effectively reducing the flow loss when the air flow enters the pre-rotation nozzle.
Description
Technical Field
The invention relates to the technical field of gas turbines, in particular to a gas turbine pneumatic hole type prewhirl nozzle with an inlet transition section.
Background
The pre-rotation cooling system is a cold air supply mode of high-temperature rotor blades commonly used in aircraft engines and combustion engines. In the prerotation cooling system, before cooling gas enters the high-temperature rotor blade to cool the high-temperature rotor blade, the cooling gas firstly flows through the prerotation nozzle, and the cooling gas coming out of the prerotation nozzle obtains a certain prerotation speed, so that the relative speed of the cooling gas and the rotor is reduced, the relative total temperature of the cooling gas is reduced, and the cooling effect is improved.
The pre-spinning nozzle is a key characteristic structure of the pre-spinning cooling system, and the characteristics of the pre-spinning nozzle are important factors influencing the pre-spinning cooling effect. The current common structural forms of the prewhirl nozzle comprise a straight round hole type, a pneumatic hole type, a vane type and the like. The flow loss of the straight round hole type pre-spinning nozzle is large, and the pre-spinning cooling effect is not ideal. Vane type pre-swirl nozzles perform well, but the structural parameters are limited by the overall design and are difficult to machine and install.
Disclosure of Invention
The invention aims to solve the technical problem of providing a pneumatic hole type prerotation nozzle of a combustion engine with an inlet transition section, aiming at the problems and the defects of a straight circular hole type prerotation nozzle and a vane type prerotation nozzle.
The technical problem to be solved by the invention is as follows:
a gas turbine pneumatic hole type pre-swirl nozzle with an inlet transition section comprises an inlet transition section and a nozzle section which are communicated in sequence; the axis of the inlet transition section intersects the axis of the nozzle section and forms an angle a, wherein a is greater than 40 DEG and less than 70 deg.
The axial line of the inlet transition section is consistent with the incoming flow direction, and the airflow does not need to be deflected when entering the inlet transition section, so that the flow separation is reduced, and the flow is more uniform. Meanwhile, the end surface area of the outlet end of the inlet transition section is larger than the cross-sectional area of the nozzle section perpendicular to the axis of the nozzle section, so that the speed of the airflow in the inlet transition section is obviously low. The inlet transition section can effectively reduce inlet flow loss.
In some possible embodiments, in order to enable the nozzle segment to realize buffering and transition effects on the air flow, the uniformity of the whole flow field in the nozzle is ensured, and the flow loss is small; the nozzle section comprises a nozzle front section, a contraction section and a nozzle rear section which are connected in sequence and have the axes on the same straight line; the end, far away from the contraction section, of the front nozzle section is communicated with the inlet transition section, the front nozzle section, the contraction section and the rear nozzle section are sequentially connected to form a spraying channel, and the diameter of the spraying channel is gradually reduced from the front nozzle section to the rear nozzle section.
In some possible embodiments, the end of the nozzle front section remote from the convergent section is elliptical, and the cross section of the nozzle front section perpendicular to the axis thereof is circular.
In some possible embodiments, the constriction section is in the shape of a circular truncated cone, and the large end of the constriction section is connected with the front nozzle section, and the diameter of the large end is equal to the diameter of a cross section of the front nozzle section perpendicular to the axis of the front nozzle section.
In some possible embodiments, the section of the nozzle rear section perpendicular to the axis thereof is circular, the diameter of which is equal to the diameter of the small end of the convergent section; the diameter of the section of the front section of the nozzle, which is vertical to the axis of the front section of the nozzle, is 1.2-2.5 times of the diameter of the rear section of the nozzle.
In some possible embodiments, in order to ensure the pre-rotation effect, the flow is not uniform due to the fact that the length-diameter ratio of the rear section of the nozzle is too small, the Cd coefficient of the pre-rotation nozzle is reduced, and the overall flow loss is increased; the length of the nozzle rear section in the axial direction thereof is at least 1.5 times its diameter.
In some possible embodiments, the diameter of the rear section of the nozzle is 5 to 15mm in order to ensure that the flow losses during the flow are reduced and that the flow inhomogeneities are reduced.
In some possible embodiments, the cross-section of the inlet transition section perpendicular to the axis thereof is kidney-shaped, the length of the long axis of the kidney-shaped transition section is greater than the long axis of the ellipse of the nozzle front section, and the short axis of the kidney-shaped transition section is greater than the short axis of the ellipse of the nozzle front section.
In some possible embodiments, the cross-section of the inlet transition section perpendicular to its axis is circular, with a diameter greater than the major axis of the ellipse of the nozzle front section.
Compared with the prior art, the invention has the beneficial effects that:
according to the pneumatic hole type pre-rotation nozzle for the pre-rotation cooling system of the combustion engine, the axis of the inlet transition section is vertical to the upstream disc surface of the pre-rotation nozzle, and airflow does not need to deflect when entering the inlet transition section from the cavity in front of the inlet transition section, so that flow separation is reduced, and the flow is more uniform; meanwhile, the cross sectional area of the inlet transition section, which is vertical to the axis, is larger than that of the nozzle section, which is vertical to the axis, so that the flow speed of the airflow in the inlet transition section is low, and the flow loss of the airflow entering the nozzle section is effectively reduced;
in the invention, the cross section area of the front section of the nozzle, which is vertical to the axis, is between the cross section areas of the inlet transition section and the rear section of the nozzle, which are vertical to the axis, and the front section of the nozzle also plays a role in transition and buffering;
in the invention, the area of the inlet of the front section of the nozzle is slightly smaller than the area of the outlet of the inlet transition section, so that the consistency of the axes of the front part and the rear part after the front part and the rear part are machined is ensured, and the flow loss of the transition section is reduced.
Drawings
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a schematic cross-sectional view of the inlet transition section and nozzle section connection of the present invention;
FIG. 3 is a schematic view of the inlet transition section of the present invention taken along a waist-shaped cross-section taken perpendicular to its axis;
FIG. 4 is a schematic structural view of a nozzle segment according to the present invention;
FIG. 5 is a schematic plan view of a nozzle segment according to the present invention;
wherein: 1. an inlet transition section; 2. a nozzle front section; 3. a contraction section; 4. a nozzle rear section; 5. an intermediate gas seal ring; 6. pre-spinning a nozzle plate; 7. the inlet of the front section of the nozzle.
Detailed Description
The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are some, but not all, embodiments of the present application. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.
To make the purpose, technical solutions and advantages of the present application clearer, the technical solutions in the present application will be clearly and completely described below with reference to the drawings in the present application, and it is obvious that the described embodiments are some, but not all embodiments of the present application. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.
The invention is further illustrated with reference to the following figures and examples.
The invention provides a gas turbine pneumatic hole type prerotation nozzle with an inlet transition section 1, which is used for providing cooling air with proper pressure, temperature and flow for a high-temperature rotor blade in a gas turbine prerotation cooling system to realize effective cooling of the high-temperature rotor blade.
The method is realized by the following technical scheme, as shown in figures 1-5,
a gas turbine pneumatic hole type prewhirl nozzle with an inlet transition section 1 comprises the inlet transition section 1 and a nozzle section which are communicated in sequence; the axis of the inlet transition section 1 intersects the axis of the nozzle section and forms an angle a, wherein a is greater than 40 DEG and less than 70 deg.
Preferably, in order to ensure that the inlet of the nozzle segment completely falls into the outlet end of the inlet transition section, the efficiency of the nozzle is greatly reduced if the inlet end of the nozzle is partially blocked by the solid wall surface, and the area of the end surface of the outlet end of the inlet transition section 1 is slightly larger than that of the end surface of the inlet end of the nozzle segment.
Wherein the outlet end of the inlet transition section 1 is connected with the inlet end of the nozzle section.
When the air flow inlet transition section is used, the axial line of the inlet transition section 1 is consistent with the incoming flow direction of the air flow, the air flow does not need to be deflected when entering the inlet transition section 1, the flow separation is reduced, and the flow is more uniform. At the same time, the cross-sectional area of the inlet transition section 1 perpendicular to the axis thereof is larger than the cross-sectional area of the nozzle section perpendicular to the axis thereof, so that the velocity of the gas flow in the inlet transition section 1 is significantly lower. Therefore, the inlet transition section 1 can effectively reduce the flow loss of the airflow inlet.
Referring to fig. 2, the axis of the inlet transition section 1 intersects the axis of the nozzle section and forms an included angle a; the angle a is more than 40 degrees and less than 70 degrees, and the reasonable value of the included angle a can effectively ensure the consistency of the circulation to ensure that the fluid flows more uniformly, thereby reducing the flow loss. Exceeding the reasonable value range leads to a small Cd (flow coefficient) of the prerotation nozzle, and an ideal prerotation effect cannot be achieved.
Preferably, in some possible embodiments, a is 60 °.
In some possible embodiments, in order to enable the nozzle segment to realize buffering and transition effects on the air flow, the uniformity of the whole flow field in the nozzle is ensured, and the flow loss is small; the nozzle section comprises a nozzle front section 2, a contraction section 3 and a nozzle rear section 4 which are sequentially connected and have the same straight line axis; the end, far away from the contraction section 3, of the nozzle front section 2 is communicated with the inlet transition section 1, the nozzle front section 2, the contraction section 3 and the nozzle rear section 4 are sequentially connected to form a spraying channel, and the diameter of the spraying channel is gradually reduced from the nozzle front section 2 to the nozzle rear section 4. The inlet end is arranged on one side of the front nozzle section 2 close to the inlet transition section 1 and is communicated with the outlet section of the inlet transition section 1.
The air current gets into from import changeover portion 1, flows into convergent section 3 and nozzle back end 4 behind the nozzle anterior segment 2, and then realizes accelerating and prewhirling.
In order to guarantee the alignment effect of 2 axes of import changeover portion 1 and nozzle anterior segment, guarantee the flow homogeneity of junction, consider the deviation that import changeover portion 1 and 2 course of working axis of nozzle anterior segment match, require that the area of 2 entry of nozzle anterior segment is slightly less than the exit area of import changeover portion 1, ensure the uniformity of its axis after two parts machining are accomplished to the front and back from this, reduce the flow loss of changeover portion, nozzle anterior segment 2 has played the effect of transition and buffering equally, the precision of processing technology will be considered in the area of nozzle anterior segment entry. After the air flow comes out from the inlet transition section 1, the air flow passes through the front section 2 of the nozzle before entering the rear section 4 of the nozzle to be pre-rotated and accelerated, so that the uniformity of the whole flow field in the nozzle can be ensured, and the flow loss is small.
In some possible embodiments, as shown in fig. 4 and 5, the end of the nozzle front section 2 away from the constriction section 3 is elliptical, that is, the nozzle front section inlet 7 is elliptical, the nozzle front section inlet 7 is the end of the nozzle front section away from the constriction section 3, and the cross section of the nozzle front section 2 perpendicular to the axis thereof is circular.
In some possible embodiments, as shown in fig. 2 and 4, the constriction 3 is in the shape of a circular truncated cone, the large end of which is connected to the nozzle front section 2 and the diameter of which is equal to the diameter of a cross section of the nozzle front section 2 perpendicular to the axis thereof.
In some possible embodiments, as shown in fig. 2, the section of the nozzle rear section 4 perpendicular to its axis is circular, with a diameter equal to the diameter of the small end of the convergent section 3; the diameter of the cross section of the front section 2 perpendicular to the axis of the nozzle is 1.2-2.5 times of the diameter of the rear section 4 of the nozzle.
The nozzle back section 4 is smaller than the nozzle front section 2 in the diameter of the cross section perpendicular to the axis and the constriction section 3 exists because the consistency of the fluid passing through the conical constriction section 3 in the nozzle back section 4 is better than that in the nozzle front section 2, and the pre-rotation effect of the overall pre-rotation nozzle is more obvious.
In some possible embodiments, to ensure the pre-swirl effect of the nozzle segment; the low length-diameter ratio of the rear section 4 of the nozzle can cause uneven flow, the Cd coefficient of the pre-rotation nozzle is reduced, and the overall flow loss is increased. The length of the nozzle rear section 4 in the axial direction thereof is at least 1.5 times its diameter.
In some possible embodiments, the nozzle rear section 4 has a diameter of 5-15 mm.
The diameter of the cross section of the nozzle rear section 4 perpendicular to the axis is too small, which results in a smaller flow coefficient and larger flow loss, and the diameter of the cross section of the nozzle rear section 4 perpendicular to the axis is too large, which results in an increased non-uniformity of the flow field, and for this purpose, the diameter of the nozzle rear section 4 is set to be 5-15 mm.
In some possible embodiments, as shown in fig. 3 and 5, the cross section of the inlet transition section 1 perpendicular to the axis thereof is kidney-shaped, that is, the inlet transition section 1 is a kidney-shaped hole, the length of the long axis Q1 of the kidney is greater than the long axis S1 of the ellipse of the nozzle front section 2, and the short axis Q2 of the kidney is greater than the short axis S2 of the ellipse of the nozzle front section 2.
The waist-shaped hole is more favorable for meeting the strength requirement of the part on the premise of the same total inlet area.
In some possible embodiments, the cross-section of the inlet transition piece 1 perpendicular to its axis is circular (not shown), i.e. the inlet transition piece 1 is a cylindrical hole with a diameter larger than the major axis S1 of the ellipse of the nozzle front section 2.
In some possible embodiments, the inlet transition section 1 is arranged on an intermediate gas seal ring 5, the nozzle section is arranged on a pre-spinning nozzle plate 6, and the intermediate gas seal ring 5 is detachably connected with the pre-spinning nozzle plate 6; the detachable connection is adopted, so that the inlet transition section 1 and the nozzle section can be independently processed, the processing difficulty is greatly reduced, and the processing performance and the repeatability are good. When the parameters of the pre-rotation nozzle need to be adjusted subsequently, only the nozzle section needs to be processed again and the pre-rotation nozzle plate 6 needs to be replaced, and the inlet transition section 1 is not affected and does not need to be changed. Thus greatly improving the processing convenience and repeatability.
Because the axial line of the inlet transition section 1 is consistent with the incoming flow direction, the air flow does not need to be deflected when entering the inlet transition section 1, the flow separation is reduced, and the flow is more uniform. Meanwhile, the cross-sectional area of the inlet transition section 1 perpendicular to the axis is far larger than that of the nozzle section perpendicular to the axis, and the speed of the airflow in the inlet transition section 1 is obviously small. The inlet transition section 1 can thus effectively reduce inlet flow losses.
The cross-sectional area of the inlet transition section 1 perpendicular to the axis is much larger than the cross-sectional area of the nozzle section perpendicular to the axis, and the velocity of the gas flow in the inlet transition section 1 is significantly smaller. The inlet transition section 1 can thus effectively reduce inlet flow losses.
The cross-sectional area of the nozzle front section 2 perpendicular to the axis is between the cross-sectional areas of the inlet transition section 1 and the nozzle rear section 4 perpendicular to the axis, so that the nozzle front section 2 also plays a role in transition and buffering.
In order to guarantee the alignment effect of 2 axes of import changeover portion 1 and nozzle anterior segment, guarantee the flow homogeneity of junction, consider the deviation that import changeover portion 1 and 2 course of working axis of nozzle anterior segment match, require that the area of 2 entry of nozzle anterior segment slightly is less than the exit area of import changeover portion 1, can ensure the uniformity of its axis after two parts machining finishes around from this, reduce the flow loss of changeover portion, the precision of processing technology is considered in the area of 2 entry of specific nozzle anterior segment. After the air flow comes out from the inlet transition section 1, the air flow passes through the front section 2 of the nozzle before entering the rear section 4 of the nozzle to be pre-rotated and accelerated, so that the uniformity of the whole flow field in the nozzle can be ensured, and the flow loss is small.
The foregoing detailed description of the embodiments of the present application has been presented, and specific examples have been applied in the present application to explain the principles and implementations of the present application, and the above description of the embodiments is only used to help understand the method and the core ideas of the present application; meanwhile, for a person skilled in the art, according to the idea of the present application, there may be variations in the specific embodiments and the application scope, and in summary, the content of the present specification should not be construed as a limitation to the present application.
Claims (9)
1. The utility model provides a take pneumatic pass of combustion engine of import changeover portion nozzle of prewhirling which characterized in that: comprises an inlet transition section and a nozzle section which are communicated in sequence; the axis of the inlet transition section intersects the axis of the nozzle section and forms an angle a, wherein a is greater than 40 DEG and less than 70 deg.
2. The gas-fired engine pneumatic hole type pre-swirl nozzle with the inlet transition section according to claim 1, characterized in that: the nozzle section comprises a nozzle front section, a contraction section and a nozzle rear section which are connected in sequence and have the axes on the same straight line; the end, far away from the contraction section, of the front nozzle section is communicated with the inlet transition section, the front nozzle section, the contraction section and the rear nozzle section are sequentially connected to form a spraying channel, and the diameter of the spraying channel is gradually reduced from the front nozzle section to the rear nozzle section.
3. The gas-fired engine pneumatic hole type pre-swirl nozzle with the inlet transition section according to claim 2, characterized in that: the end of the front nozzle section, which is far away from the contraction section, is elliptical, and the cross section of the front nozzle section, which is perpendicular to the axis of the front nozzle section, is circular.
4. The gas-fired engine pneumatic hole type pre-swirl nozzle with the inlet transition section according to claim 3, characterized in that: the contraction section is in a round table shape, the large end of the contraction section is connected with the front nozzle section, and the diameter of the large end is equal to the diameter of the section, perpendicular to the axis, of the front nozzle section.
5. A gas turbine pneumatic hole type pre-rotation nozzle with an inlet transition section according to claim 3 or 4, characterized in that: the section of the rear section of the nozzle, which is perpendicular to the axis of the rear section of the nozzle, is in a circular shape, and the diameter of the rear section of the nozzle is equal to that of the small end of the contraction section; the diameter of the section of the front section of the nozzle, which is vertical to the axis of the front section of the nozzle, is 1.2-2.5 times of the diameter of the rear section of the nozzle.
6. The gas-fired engine pneumatic hole type pre-swirl nozzle with the inlet transition section according to claim 5, characterized in that: the length of the nozzle rear section in the axial direction thereof is at least 1.5 times its diameter.
7. The gas-fired engine pneumatic hole type pre-swirl nozzle with the inlet transition section according to claim 6, characterized in that: the diameter of the rear section of the nozzle is 5-15 mm.
8. The gas-fired engine pneumatic hole type pre-swirl nozzle with the inlet transition section according to claim 2, characterized in that: the cross section of the inlet transition section, which is vertical to the axis of the inlet transition section, is in a waist shape, the length of a long shaft of the waist shape is larger than that of the long shaft of the front section of the nozzle, and a short shaft of the waist shape is larger than that of the front section of the nozzle.
9. The gas-fired engine pneumatic hole type pre-swirl nozzle with the inlet transition section according to claim 2, characterized in that: the cross section of the inlet transition section, which is vertical to the axis of the inlet transition section, is circular, and the diameter of the inlet transition section is larger than the long axis of the oval shape of the front section of the nozzle.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011318439.0A CN112412544A (en) | 2020-11-23 | 2020-11-23 | Gas turbine pneumatic hole type prerotation nozzle with inlet transition section |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202011318439.0A CN112412544A (en) | 2020-11-23 | 2020-11-23 | Gas turbine pneumatic hole type prerotation nozzle with inlet transition section |
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Application publication date: 20210226 |
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