CN112065588B - Flow adjusting method of swirl vane type prewhirl nozzle for aircraft engine - Google Patents

Abstract

A flow adjusting method of a swirl vane type prewhirl nozzle for an aeroengine comprises the following steps: carrying out flow simulation adjustment on the pre-rotation nozzle three-dimensional model to determine an adjustment amount; according to an adjustment principle of avoiding tearing damage and irreparable damage of the swirl vane, a torsion adjustment mode, an adjustment mode combining torsion and grinding removal or an adjustment mode combining torsion and surfacing welding is adopted for the swirl vane; when the difference between the flow measurement value of the pre-swirl nozzle and the design standard value is less than or equal to 10 percent, the swirl vanes adopt a torsion adjustment mode; when the difference between the flow measured value of the pre-swirl nozzle and the design standard value is more than 10%, the swirl vanes adopt an adjusting mode of combining torsion and grinding removal or an adjusting mode of combining torsion and surfacing welding. The invention effectively solves the problem of adjusting the pre-rotation nozzle in the flow test inspection process, ensures that the test flow value is qualified and meets the design requirement, fully exerts the cooling capacity of the pre-rotation nozzle and achieves the cooling effect on the turbine part.

Description

Flow adjusting method of swirl vane type prewhirl nozzle for aircraft engine

Technical Field

The invention belongs to the technical field of aero-engines, and particularly relates to a flow adjusting method of a swirl vane type pre-swirl nozzle for an aero-engine.

Background

With the continuous pursuit of the aero-engine for efficiency and unit thrust, the inlet temperature of the turbine is continuously improved and far exceeds the limit temperature which can be borne by high-temperature resistant materials, and the multi-type aero-engine can reduce the temperature of turbine parts by applying a prerotation technology, and the principle is as follows: the prerotation structure is utilized to expand the airflow in the prerotation nozzle so as to reduce the static temperature of the airflow, obtain the same circumferential speed as the rotation direction of the turbine rotor component, reduce the relative speed of the cold air, and achieve the aims of reducing the relative total temperature and improving the cooling quality of the cold air for the turbine rotor component.

The air circulation capacity and the outlet airflow parameters of the pre-rotation nozzle are critical to the cooling efficiency of the turbine part, and directly influence the safe work and the service life of the turbine part, so that the flow of the pre-rotation nozzle must be tested and checked, and the pre-rotation nozzle can be used for an aeroengine only after the flow is regulated to be qualified. However, a flow rate adjusting method for the pre-swirl nozzle is not explicitly proposed, and how to implement the flow rate of the pre-swirl nozzle as an important link of test inspection becomes a critical problem of whether the flow rate of the pre-swirl nozzle is qualified or not.

Disclosure of Invention

Aiming at the problems in the prior art, the invention provides a flow adjusting method of a swirl vane type prewhirl nozzle for an aeroengine, which effectively solves the problem of adjusting the prewhirl nozzle in the flow test checking process, ensures that the test flow value is qualified, meets the design requirement, fully exerts the cooling capacity of the prewhirl nozzle and achieves the cooling effect on turbine parts; the nozzle structure redundant repair and even irreparable damage caused by the previous blind operation are avoided, the waste of production resources is avoided, the flow can quickly and accurately reach the test target value, and the production working efficiency is improved; the requirement for circumferential uniformly distributed adjustment is stipulated, the adjustment degree of each blade and each flow channel is ensured to be the same, the uniform temperature distribution and the uniform cooling effect of cooling air flowing out through the pre-rotation nozzle are ensured, and the thermal stress hazard caused by the concentrated cooling of turbine parts is avoided.

In order to achieve the purpose, the invention adopts the following technical scheme: a flow adjusting method of a swirl vane type pre-swirl nozzle for an aeroengine comprises the following steps:

the method comprises the following steps: carrying out three-dimensional modeling on the pre-spinning nozzle, carrying out simulation adjustment on a three-dimensional model of the pre-spinning nozzle, analyzing the change of the interception area of the pre-spinning nozzle until the flow value meets the design requirement, and then determining the adjustment quantity of the pre-spinning nozzle according to the result of the simulation adjustment;

step two: according to an adjustment principle of avoiding tearing damage and irreparable damage of the swirl vane, a torsion adjustment mode, an adjustment mode combining torsion and grinding removal or an adjustment mode combining torsion and surfacing welding is adopted for the swirl vane; when the difference between the flow measurement value of the pre-swirl nozzle and the design standard value is less than or equal to 10 percent, the swirl vanes adopt a torsion adjustment mode; when the difference between the flow measured value of the pre-swirl nozzle and the design standard value is more than 10%, the swirl vanes adopt an adjusting mode of combining torsion and grinding removal or an adjusting mode of combining torsion and surfacing welding;

firstly, when the swirl vane adopts a torsion adjusting mode, preparing a clamp-type tool, selecting a swirl vane, attaching a positioning surface of a reference rod of the clamp-type tool to the outer end surface of the annular inner shell, attaching a positioning surface of a torsion rod of the clamp-type tool to the surface of the tail part of the swirl vane, applying grip to the clamp-type tool, wrenching the tail part of the swirl vane by the torsion rod, marking a wrenching angle by a dial scale until the opening adjustment of the tail part of the swirl vane reaches a set value; other swirl blades are selected alternatively to implement the same adjusting process, all selected swirl blades are ensured to be uniformly distributed in the circumferential direction, and the flow interception area is changed after the swirl blades are adjusted, so that the flow adjustment is finally realized;

secondly, when the flow rate of the swirl vane does not reach the design standard value after being adjusted by torsion, a grinding removal adjustment mode is further adopted, firstly, one swirl vane is selected, the tail edge of the swirl vane is taken as the starting point, a scribed line is drawn along the profile direction of the swirl vane so as to determine the end position of the adjustment amount, and then the tail edge of the swirl vane is removed to the scribed line by grinding with a small electric drill, so that the interception area of the swirl vane is enlarged, and the circulation capacity is enhanced; other swirl blades are selected alternatively to implement the same adjusting process, all the selected swirl blades are ensured to be uniformly distributed in the circumferential direction, and the grinding and cutting degrees of the swirl blades from the blade root to the blade height direction are ensured to be completely the same;

thirdly, when the flow rate of the swirl vanes after being adjusted by torsion still does not reach the design standard value, a surfacing adjustment mode is further adopted, two adjacent swirl vanes are selected firstly, then the cooling air channel is subjected to surfacing plugging by argon arc welding, and surfacing between the two swirl vanes cannot be interrupted, so that the welding strength is prevented from failing to reach the standard, surfacing welding materials are prevented from falling off to damage the rotor component, the interception area of the swirl vanes is reduced, and the flow capacity is reduced; and other groups of swirl blades are selected alternatively to implement the same adjusting process, the selected swirl blades are uniformly distributed in the circumferential direction, and the height of all surfacing positions is kept consistent.

The invention has the beneficial effects that:

the flow adjusting method of the swirl vane type prewhirl nozzle for the aeroengine effectively solves the problem of adjusting the prewhirl nozzle in the flow test checking process, ensures that the test flow value is qualified and meets the design requirement, fully exerts the cooling capacity of the prewhirl nozzle and achieves the cooling effect on turbine parts; the nozzle structure redundant repair and even irreparable damage caused by the previous blind operation are avoided, the waste of production resources is avoided, the flow can quickly and accurately reach the test target value, and the production working efficiency is improved; the requirement for circumferential uniformly distributed adjustment is stipulated, the adjustment degree of each blade and each flow channel is ensured to be the same, the uniform temperature distribution and the uniform cooling effect of cooling air flowing out through the pre-rotation nozzle are ensured, and the thermal stress hazard caused by the concentrated cooling of turbine parts is avoided.

Drawings

FIG. 1 is a schematic structural view of a swirl vane type pre-swirl nozzle in an embodiment;

FIG. 2 is a view taken along line A of FIG. 1;

FIG. 3 is a schematic view of a torsional adjustment mode;

FIG. 4 is a schematic illustration of a grinding cut adjustment;

FIG. 5 is a schematic view of a weld overlay adjustment;

in the figure, 1-annular inner shell, 2-annular outer shell, 3-swirl vane, 4-combustion chamber casing, 5-clamp fixture, 5.1-reference rod, 5.2-torsion rod, 5.3-dial scale, 6-grinding cut-off part and 7-surfacing part.

Detailed Description

The invention is described in further detail below with reference to the figures and the specific embodiments.

As shown in fig. 1 and 2, the swirl vane type pre-swirl nozzle disclosed in this embodiment is composed of an annular inner casing 1, an annular outer casing 2, and a plurality of swirl vanes 3, wherein the annular inner casing 1 and the annular outer casing 2 are coaxially welded in a stack at the end of a casing 4 in a combustion chamber, all the swirl vanes 3 are uniformly welded at the gap between the annular inner casing 1 and the annular outer casing 2 along the circumferential direction, and a cooling air passage is formed between adjacent swirl vanes 3. When the flow value of the pre-rotation nozzle does not meet the design requirement through test determination, the flow of the pre-rotation nozzle needs to be adjusted, and the specific adjustment mode is as follows:

a flow adjusting method of a swirl vane type pre-swirl nozzle for an aeroengine comprises the following steps:

the method comprises the following steps: carrying out three-dimensional modeling on the pre-spinning nozzle, carrying out simulation adjustment on a three-dimensional model of the pre-spinning nozzle, analyzing the change of the interception area of the pre-spinning nozzle until the flow value meets the design requirement, and then determining the adjustment quantity of the pre-spinning nozzle according to the result of the simulation adjustment;

step two: according to the regulation principle of avoiding tearing damage and irreparable damage of the swirl vane 3, a torsion regulation mode, a regulation mode combining torsion and grinding removal or a regulation mode combining torsion and surfacing welding is adopted for the swirl vane 3; when the difference between the flow measurement value of the pre-swirl nozzle and the design standard value is less than or equal to 10 percent, the swirl vanes 3 adopt a torsion adjustment mode; when the difference between the flow measured value of the pre-swirl nozzle and the design standard value is more than 10%, the swirl vanes 3 adopt an adjusting mode combining torsion and grinding removal or an adjusting mode combining torsion and surfacing;

firstly, when the swirl vane 3 adopts a torsion adjusting mode, a clamp-type tool 5 needs to be prepared, one swirl vane 3 is selected, as shown in fig. 3, a positioning surface of a reference rod 5.1 of the clamp-type tool 5 is attached to the outer end surface of the annular inner shell 1, a positioning surface of a torsion rod 5.2 of the clamp-type tool 5 is attached to the surface of the tail of the swirl vane 3, a holding force is applied to the clamp-type tool 5, the tail of the swirl vane 3 is twisted by the torsion rod 5.2, and the twisting angle is marked by a dial 5.3 until the opening adjustment of the tail of the swirl vane 3 reaches a set value; other swirl blades 3 are selected alternatively to implement the same adjusting process, all the selected swirl blades 3 are ensured to be uniformly distributed in the circumferential direction, and the flow interception area of the swirl blades 3 is changed after adjustment, so that the flow adjustment is finally realized;

secondly, when the flow rate of the swirl blade 3 does not reach the design standard value after being adjusted by torsion, a grinding removal adjustment mode is further adopted, firstly, one swirl blade 3 is selected, the tail edge of the swirl blade 3 is taken as the starting point, a scribed line is drawn along the profile direction of the swirl blade 3 to determine the end position of the adjustment amount, then, the tail edge of the swirl blade 3 is grinded and removed to the scribed line position by using a small electric drill, as shown in fig. 4, so that the interception area of the swirl blade 3 is enlarged, and the circulation capacity is enhanced; other swirl blades 3 are selected alternatively to implement the same adjusting process, all the selected swirl blades 3 are ensured to be uniformly distributed in the circumferential direction, and the grinding and cutting degrees of the swirl blades 3 from the blade root to the blade height direction are ensured to be completely the same;

thirdly, when the flow rate of the swirl vanes 3 is not yet up to the design standard value after being adjusted by torsion, a surfacing adjustment mode is further adopted, two adjacent swirl vanes 3 are selected firstly, then the cooling air channel is subjected to surfacing plugging by argon arc welding, and surfacing between the two swirl vanes 3 cannot be interrupted, as shown in fig. 5, the condition that the welding strength does not reach the standard and surfacing welding materials fall off to damage a rotor component is prevented, so that the interception area of the swirl vanes 3 is reduced, and the circulation capacity is reduced; and other groups of swirl blades 3 are alternatively taken to implement the same adjusting process, the selected swirl blades 3 are ensured to be uniformly distributed in the circumferential direction, and the height of all surfacing positions is ensured to be consistent.

Specifically, for the swirl vane type pre-swirl nozzle shown in fig. 1 and 2, an empirical data of the adjustment amount is summarized in combination with the actual work, as shown in the following table:

TABLE 1

In the above table, the empirical data in the torsion adjustment mode and the grinding removal adjustment mode are obtained by adjusting all the swirl vanes 3, and the empirical data in the overlay welding adjustment mode is obtained by adjusting the overlay welding positions uniformly distributed at 8 positions. When the flow measured value is lower than the design standard value and the twisting adjustment mode is adopted, if the flow still does not reach the design standard value when the twisting angle of the rotational flow blade 3 is increased and adjusted by 3.5 degrees, the twisting angle of the rotational flow blade 3 is not increased any more, the blade tearing caused by the overlarge twisting angle is prevented, and then the grinding removal adjustment mode is further adopted until the flow is adjusted to be consistent with the design standard value. On the contrary, when the flow measurement value is higher than the design standard value and a torsion adjusting mode is adopted, if the flow rate still does not reach the design standard value when the wrenching angle of the swirl vanes 3 is reduced and adjusted by 3.5 degrees, the wrenching angle of the swirl vanes 3 is not reduced any more, the tearing of the vanes caused by the overlarge wrenching angle is prevented, then a surfacing adjusting mode is further adopted until the flow rate is adjusted to be consistent with the design standard value, and in the surfacing adjusting process, a small part of cooling air channels are allowed to be completely blocked by surfacing.

The embodiments are not intended to limit the scope of the present invention, and all equivalent implementations or modifications without departing from the scope of the present invention are intended to be included in the scope of the present invention.

Claims (1)

1. A flow adjusting method of a swirl vane type pre-swirl nozzle for an aeroengine is characterized by comprising the following steps:

the method comprises the following steps: carrying out three-dimensional modeling on the pre-spinning nozzle, carrying out simulation adjustment on a three-dimensional model of the pre-spinning nozzle, analyzing the change of the interception area of the pre-spinning nozzle until the flow value meets the design requirement, and then determining the adjustment quantity of the pre-spinning nozzle according to the result of the simulation adjustment; the prewhirl nozzle consists of an annular inner shell, an annular outer shell and a plurality of whirl blades, and the annular inner shell and the annular outer shell are coaxially welded at the tail end of the casing in the combustion chamber in a stacked mode;

step two: according to an adjustment principle of avoiding tearing damage and irreparable damage of the swirl vane, a torsion adjustment mode, an adjustment mode combining torsion and grinding removal or an adjustment mode combining torsion and surfacing welding is adopted for the swirl vane; when the difference between the flow measurement value of the pre-swirl nozzle and the design standard value is less than or equal to 10 percent, the swirl vanes adopt a torsion adjustment mode; when the difference between the flow measured value of the pre-swirl nozzle and the design standard value is more than 10%, the swirl vanes adopt an adjusting mode of combining torsion and grinding removal or an adjusting mode of combining torsion and surfacing welding;

firstly, when the swirl vane adopts a torsion adjusting mode, preparing a clamp-type tool, selecting a swirl vane, attaching a positioning surface of a reference rod of the clamp-type tool to the outer end surface of the annular inner shell, attaching a positioning surface of a torsion rod of the clamp-type tool to the surface of the tail part of the swirl vane, applying grip to the clamp-type tool, wrenching the tail part of the swirl vane by the torsion rod, marking a wrenching angle by a dial scale until the opening adjustment of the tail part of the swirl vane reaches a set value; other swirl blades are selected alternatively to implement the same adjusting process, all selected swirl blades are ensured to be uniformly distributed in the circumferential direction, and the flow interception area is changed after the swirl blades are adjusted, so that the flow adjustment is finally realized;

secondly, when the flow rate of the swirl vane does not reach the design standard value after being adjusted by torsion, a grinding removal adjustment mode is further adopted, firstly, one swirl vane is selected, the tail edge of the swirl vane is taken as the starting point, a scribed line is drawn along the profile direction of the swirl vane so as to determine the end position of the adjustment amount, and then the tail edge of the swirl vane is removed to the scribed line by grinding with a small electric drill, so that the interception area of the swirl vane is enlarged, and the circulation capacity is enhanced; other swirl blades are selected alternatively to implement the same adjusting process, all the selected swirl blades are ensured to be uniformly distributed in the circumferential direction, and the grinding and cutting degrees of the swirl blades from the blade root to the blade height direction are ensured to be completely the same;

thirdly, when the flow rate of the swirl vanes after being adjusted by torsion still does not reach the design standard value, a surfacing adjustment mode is further adopted, two adjacent swirl vanes are selected firstly, then the cooling air channel is subjected to surfacing plugging by argon arc welding, and surfacing between the two swirl vanes cannot be interrupted, so that the welding strength is prevented from failing to reach the standard, surfacing welding materials are prevented from falling off to damage the rotor component, the interception area of the swirl vanes is reduced, and the flow capacity is reduced; and other groups of swirl blades are selected alternatively to implement the same adjusting process, the selected swirl blades are uniformly distributed in the circumferential direction, and the height of all surfacing positions is kept consistent.

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