JP5118653B2 - Turbine blade arrangement method, apparatus, and program - Google Patents

Description

  The present invention relates to a turbine blade arrangement method, apparatus, and program.

Conventionally, it has been considered important for turbine rotors used in turbochargers, gas turbines, and the like to keep shaft bending and misalignment within allowable values in order to prevent shaft breakage accidents and the like.
In the operation of implanting the turbine rotor blades in the rotor disk, the total weight of the turbine rotor blades is measured, and after the turbine rotor blades are implanted in a balanced manner in the rotor disk, the balance of the entire turbine rotor including the rotor disk is adjusted. And in the operation | work which adjusts, the method of removing an imbalance by operating a grinder and shaving a rotor disk manually is known.

JP-A-60-25670

  However, in the conventional method, the unbalance removal operation of the rotor disk using the grinder is an operation that requires experience, and has a problem that it depends on the skill of the operator. Further, it takes time to balance the rotor disk by the grinder, and there is a problem that the unbalance amount must be measured many times.

  The present invention has been made to solve the above-described problem, and provides a turbine rotor blade arrangement method, apparatus, and program that can reduce the time required for unbalance removal of a turbine rotor blade and can be easily performed. The purpose is to provide.

  In order to solve the above problems, the present invention employs the following means.

The present invention relates to a method for arranging turbine rotor blades in a turbine rotor formed by mounting a plurality of turbine rotor blades in the circumferential direction of the rotor disk , based on the position of the eccentric center of gravity and the amount of eccentric center of gravity of the rotor disk. The first process of measuring the rotor unbalance amount and the plurality of turbine blades are grouped by a predetermined number, and the unbalance amount is zero so that the turbine blades in the same group are equally spaced. The rotor disk is formed on the basis of a second process of forming a blade set by attaching to the support member and calculating the unbalance amount of the blade set, and the rotor unbalance amount and the unbalance amount of each blade set. wherein as rotor unbalance amount is reduced, the turbine blade and a third step of placing each wings set with respect to the rotor disk To provide a placement method.

According to such a configuration, the rotor unbalance amount is measured based on the position of the eccentric center of gravity of the rotor disk of the turbine and the amount of eccentric center of gravity in the first process, and a plurality of turbine rotor blades are in a predetermined number in the second process. The blades are grouped one by one, and turbine blades in the same group are attached to the support member at equal intervals in an arbitrary arrangement to form a blade set, and an unbalance amount of the blade set is calculated. Here, since the unbalance amount of the support member is zero, the unbalance amount of the blade set is a value that takes into account only the weight of the turbine blade.
In the third process, the blade arrangement is determined so that the rotor unbalance amount of the rotor disk is reduced. As a result, an arrangement that cancels out the total amount of unbalance amounts of the turbine rotor blades and the unbalance amount of the rotor disk is specified, so that the unbalance amount of the entire turbine rotor including the rotor disk can be reduced.
Further, the rotor unbalance amount can be easily grasped by measuring the rotor unbalance amount based on the position of the eccentric gravity center and the eccentric gravity center amount.

  In the turbine blade arrangement method, in the second process, the plurality of turbine blades may be grouped in order of lightness or heavyness based on the weight of each turbine blade.

  Thus, since each group is comprised by the turbine blade of substantially the same weight, the unbalance amount in each blade set can be reduced.

  In the turbine blade arrangement method, in the third step, the combination of the arrangement of the blade sets is changed, the unbalance amount of the turbine rotor in each case is calculated, and the unbalance amount is minimized. The arrangement may be specified.

  In this way, the arrangement combination of each blade set is changed, the unbalance amount of the turbine rotor for each combination is calculated, and the arrangement that minimizes the unbalance amount is calculated, so the unbalance amount is minimized. A suitable arrangement can be identified.

The present invention relates to a turbine rotor blade arrangement device in a turbine rotor formed by mounting a plurality of turbine rotor blades in the circumferential direction of a rotor disk, and acquires a rotor unbalance amount that is an unbalance amount of a rotor disk. The data acquisition means and the plurality of turbine blades are grouped by a predetermined number, and the turbine blades in the same group are attached to a support member having an unbalance amount of zero so that the turbine blades in the same group are equally spaced. forming a blade set, and calculating means for calculating the unbalance amount of the blade sets, respectively, on the basis of the unbalanced weight of the rotor unbalance amount and the wings set, the rotor unbalance amount of the rotor disk Positioning means for positioning the blade set relative to the rotor disk so as to be reduced Providing an arrangement device Ndotsubasa.

  In the above-described turbine rotor blade arrangement apparatus, in the calculation means, the plurality of turbine rotor blades may be grouped in order of lightness or heavyness based on the weight of each turbine blade.

  In the turbine blade arrangement device, the arrangement means changes the combination of the arrangement of the blade sets, calculates the unbalance amount of the turbine rotor in each case, and arranges the unbalance amount to be minimum. It is good also as specifying.

In the turbine rotor blade arrangement apparatus, the data acquisition unit may measure the rotor unbalance amount based on the position of the eccentric gravity center and the eccentric gravity center amount.

The present invention is a turbine rotor blade arrangement program in a turbine rotor formed by mounting a plurality of turbine rotor blades in a circumferential direction of a rotor disk, and acquires a rotor unbalance amount that is an unbalance amount of a rotor disk. The first treatment and the plurality of turbine blades are grouped by a predetermined number, and the turbine blades in the same group are attached to a support member having an unbalance amount of zero so that the turbine blades in the same group are equally spaced. forming a blade set, a second process for calculating the unbalance amount of the blade set respectively, based on the unbalanced weight of the rotor unbalance amount and the wings set, the rotor unbalance amount of the rotor disk A third process of arranging the blade set with respect to the rotor disk so as to reduce Providing a turbine rotor blade placement program.

  According to the present invention, it is possible to shorten the time required for the unbalance removal operation of the turbine rotor blade and to perform it easily.

It is the perspective view which showed an example of arrangement | positioning of the turbine rotor blade determined by the turbine rotor blade arrangement | positioning apparatus of this invention. It is the front view which showed an example of arrangement | positioning of the turbine rotor blade determined by the turbine rotor blade arrangement | positioning apparatus of this invention. It is the block diagram which showed an example of the hardware constitutions of the arrangement | positioning apparatus based on this invention. It is a functional block diagram of the arrangement device of the turbine rotor blade concerning the present invention. It is the figure which showed the amount of rotor unbalance by the vector. It is the figure which showed the turbine blade unbalance amount by the vector. It is a figure for demonstrating arrangement | positioning with a rotor disk and a wing | blade set. It is the figure which showed the operation | movement flow of the arrangement | positioning apparatus of the turbine rotor blade which concerns on this invention. It is the figure which showed the result of having adjusted the unbalance amount with the conventional method and the method of this invention. It is the figure which showed the adjustment result of the unbalance amount.

  Hereinafter, an embodiment of a turbine rotor blade arrangement method, apparatus, and program according to the present invention will be described with reference to the drawings.

  The turbine rotor blade arrangement device according to the present embodiment is a turbine rotor in which a plurality of turbine rotor blades are planted at regular intervals in the circumferential direction of the rotor disk. , An apparatus used to determine its optimal placement. FIG. 1 is a perspective view of a part of the turbine rotor, and FIG. 2 is a front view of a part of the turbine rotor.

As shown in FIG. 3, a turbine blade arrangement device (hereinafter referred to as “arrangement device”) 100 according to the present embodiment is a computer system (computer system), and includes a CPU (central processing unit) 1, a RAM ( Random Access Memory) and other main storage devices 2, auxiliary storage devices 3, input devices 4 such as keyboards and mice, output devices 5 such as monitors and printers, and communication for communicating information by communicating with external devices The apparatus 6 is configured.
The auxiliary storage device 3 is a computer-readable recording medium such as a magnetic disk, a magneto-optical disk, a CD-ROM, a DVD-ROM, or a semiconductor memory. The auxiliary storage device 3 stores various programs (for example, a turbine rotor blade arrangement program), and the CPU 1 reads out the program from the auxiliary storage device 3 to the main storage device 2 and executes various programs. Is realized.

  FIG. 4 is a functional block diagram showing the functions provided in the placement apparatus 100 in an expanded manner. As shown in FIG. 4, the arrangement device 100 includes a data acquisition unit (data acquisition unit) 10, a calculation unit (calculation unit) 11, and an arrangement unit (arrangement unit) 12.

  The data acquisition unit 10 acquires the rotor unbalance amount (moment) of the rotor disk. Specifically, the rotor unbalance amount is measured by the position of the eccentric gravity center and the eccentric gravity center amount, and the value is input via the input device 4 or the like, thereby acquiring the rotor unbalance amount of the rotor disk. . The rotor unbalance amount of the rotor disk is calculated, for example, by performing a test using a dedicated device. The rotor unbalance amount is represented by a vector as shown in FIG.

  The calculating unit 11 groups a plurality of turbine rotor blades by a predetermined number, and attaches the turbine rotor blades in the same group to a support member having an unbalance amount of zero so that the turbine rotor blades are equidistant in an arbitrary arrangement. A set is formed, and the unbalance amount of each wing set is calculated. This process is performed by simulation.

For example, when there are 20 turbine blades, 5 blades are grouped in order of heavier turbine blades to form 4 groups, and in each group, the turbine blades are arranged at the apex of a regular pentagon and a blade set is arranged. Generate and calculate the unbalance amount of each wing set.
Thus, by grouping in order of weight, each blade set can be constituted by turbine blades having substantially the same weight, and the unbalance amount in each blade set can be reduced.

In each blade set, the turbine blades are arranged so that the unbalance amount is minimized. For example, in the present embodiment, as shown in FIG. 6, the regular pentagons are arranged in descending order of weight. The numbers on the apexes of the pentagon in FIG. 6 indicate the order of increasing weight of the turbine blades to be embedded.
When the blade 11 is generated by arranging the heavy turbine blades on the support member diagonally as described above, the calculation unit 11 calculates the unbalance amount of the blade set.

  Information on the unbalance amount of each blade set is output to the placement unit 12.

  The placement unit 12 is configured to reduce the rotor unbalance amount of the rotor disk based on the rotor unbalance amount acquired by the data acquisition unit 10 and the unbalance amount of each blade set calculated by the calculation unit 11. Place the wing set on the rotor disk. Specifically, when all four blade sets are arranged on the rotor disk, the arrangement position of each blade set that most cancels the rotor unbalance amount is specified. In other words, an arrangement that minimizes the unbalance amount of the entire turbine rotor including the rotor disk is specified by simulation, and each blade set is arranged on the rotor disk according to the specified arrangement. FIG. 7 is a diagram showing an example of an arrangement position where the unbalance amount of the entire turbine rotor is minimized based on the rotor disk amount and the unbalance amount of each blade set.

  For example, in the case where four blade sets are evenly arranged at 360 degrees per rotation, the blade sets are arranged at intervals of 360 ° / 4 = 90 °. For example, when there are 35 turbine rotor blades, seven blade sets of five each are formed, and each blade set is arranged with an interval of 360 ° / 7 = 51.429 °. As described above, the arrangement interval of the blade sets is variable depending on the number of groups to be formed.

The placement unit 12 calculates the unbalance amount of the turbine rotor as a whole for all possible combinations of placements while sequentially changing the placement of each blade set with respect to the rotor disk, and makes the placement that minimizes this unbalance amount. Identify.
Subsequently, the placement unit 12 determines whether or not the unbalance amount in the specified placement is within an allowable range. As a result of the determination, if the unbalance amount is within the allowable range, the arrangement is adopted as the turbine rotor blade.

  When the unbalance amount of the entire turbine rotor is outside the allowable value range, the arrangement unit 12 newly adds five turbine blades from other turbine blades that are not the target 20 turbine blades. Is extracted to create one new wing set, and the calculation unit repeats the measurement of the unbalance amount for each wing set.

In the turbine rotor blade arrangement device according to the present embodiment, when the unbalance amount is outside the allowable range, the number of blade sets newly created by the arrangement unit 12 is one, but the present invention is not limited to this. For example, two new wing sets may be created, or all wing sets may be recreated.
Also, instead of re-extracting all five turbine blades in the blade set, a part of the number of turbine blades in the blade set is replaced with a new turbine blade to create a new blade set. It is good as well.

Next, the effect | action of this embodiment is demonstrated using FIG.
In the present embodiment, there will be described a case where there are 20 turbine blades and four blade sets of 5 each are formed.

  First, the center of gravity of only the rotor disk is measured, and the unbalance amount (moment) of the rotor before planting the turbine rotor blade is measured and acquired by the data acquisition unit 10 (step SA1). Subsequently, the weight of each turbine blade is measured for all turbine blades (step SA2). Four blade sets A to D are made in descending order of weight from all turbine rotor blades. In each group, the unbalance amount when the turbine rotor blades are arranged on the support member at equal intervals is analyzed (simulation) ) (Step SA3). Subsequently, an arrangement position where the total unbalance amount of the four blade sets A to D and the rotor unbalance amount are offset is specified (step SA4). Turbine blades are planted in the rotor with the specified arrangement (step SA5).

When turbine rotor blades are planted in the rotor, the unbalance amount of the entire turbine rotor is measured, and it is determined whether or not the unbalance amount is within an allowable value range. If the unbalance amount is within the allowable value range, the process is terminated (step SA6).
If the unbalance amount is outside the allowable value range, new turbine blades are extracted from other turbine blades that are not the 20 turbine blades handled in this process (step SA7), and the process returns to step SA2. This process is repeated.

As described above, according to the turbine rotor blade arrangement device according to the present embodiment, the rotor unbalance amount of the rotor disk is measured, and each blade set grouped in descending order of the weight of the turbine rotor blades. The unbalance amount of each blade set is measured, and the combination of the arrangement of the rotor disk and each blade set such that the total unbalance amount of each blade set and the unbalance amount of the rotor disk cancel each other is calculated. In this way, the unbalance amount is adjusted so that the unbalance amount of the rotor disk and the total unbalance amount of each blade set are balanced.
This eliminates the unbalance removal work using the grinder and eliminates the grinder powder removal work when the unbalance removal work is performed by the grinder, so that the time required for the balance work can be reduced.

  Further, according to the arrangement device of the present embodiment, the unbalance amount for each blade set is calculated, and based on this, the arrangement of the blade set is specified so as to cancel out the unbalance amount of the rotor disk, and the whole including the rotor disk Measure the amount of unbalance. This makes it possible to reduce the number of times the unbalance amount is measured. Furthermore, since the arrangement with the minimum unbalance amount is specified based on the rotor unbalance amount and the unbalance amount of each blade set, balancing can be performed efficiently.

  Further, according to the turbine rotor blade arrangement device in the present embodiment, since the unbalance removal work by the grinder that requires skill is unnecessary, the balance work can be performed as planned without depending on the operator. It can lead to improvement of CS (Customer Satisfaction: Customer Satisfaction).

Next, an example of the result of comparing the adjustment result of the unbalance amount by the turbine rotor blade arrangement apparatus 100 according to the present embodiment and the adjustment result of the unbalance amount by the conventional method with the optimum arrangement will be shown.
The case where the rotor unbalance amount is 21.5 cm away from the center position, the phase is 102 degrees, and the weight is 16 grams will be described. As shown in FIG. 9, the unbalance amount of the optimal arrangement that can be balanced at this time is 4.52 grams, and the unbalance amount after adjustment by the placement device 100 is 4.13 grams. On the other hand, when this rotor unbalance amount is adjusted by the conventional method, the unbalance amount is 22.41 grams. This result is shown in FIG. Thus, as can be seen from FIG. 10, it can be seen that a value close to the optimum placement is calculated by the adjustment by the placement device 100 according to the present embodiment.

Further, for example, in the arrangement device 100 according to the present embodiment, the arrangement unit 12 determines a suitable arrangement of the blade sets by simulation. At this time, for example, assuming that seven blade sets are generated from 35 turbine blades and these seven blade sets are attached to the rotor disk, the entire arrangement of the seven blade sets is 2 (pentagonal). two ways) × ₇ P ₇ (total arrangement) / 2 = 5040 becomes (street). For example, 5040 kinds of calculations can be made within 1 minute with a CPU of 2.8 GHz. Therefore, the optimal arrangement of the blade sets can be obtained in such a short time.

  In the present embodiment, the calculation unit 11 groups the turbine rotor blades in order from the heaviest blades, but is not limited thereto. For example, the turbine rotor blades may be grouped in order from the lighter blade.

  Further, in the present embodiment, the calculation unit 11 divides the turbine blades into five for each group of turbine blades, but the number of turbine blades in one group is not particularly limited. The number of turbine blades in one group may be a number that can be divided by the number of all turbine blades.

10 Data Acquisition Unit 11 Calculation Unit 12 Arrangement Unit 100 Turbine Rotor Arrangement Device

Claims (8)

A method for arranging turbine blades in a turbine rotor formed by mounting a plurality of turbine blades in a circumferential direction of a rotor disk,
A first process of measuring the rotor unbalance amount based on the position of the eccentric center of gravity and the amount of eccentric center of gravity of the rotor disk;
A plurality of the turbine blades are grouped by a predetermined number, and a blade set is formed by attaching the turbine blades in the same group to a support member having an unbalance amount of zero so that the turbine blades are equally spaced in an arbitrary arrangement. , A second process of calculating the unbalance amount of each wing set,
On the basis of the unbalance of the rotor unbalance amount and the wings set, so that the rotor unbalance amount of the rotor disk is reduced, a third step of placing each wings set with respect to the rotor disk And a method for arranging the turbine rotor blades.   2. The method for arranging turbine blades according to claim 1, wherein in the second step, the plurality of turbine blades are grouped in a light order or a heavy order based on the weight of each turbine blade.   In the third step, the combination of the arrangements of the blade sets is changed, the unbalance amount of the turbine rotor in each case is calculated, and the arrangement that minimizes the unbalance amount is specified. Item 3. A turbine rotor blade arrangement method according to Item 2. A turbine rotor blade arrangement device in a turbine rotor formed by mounting a plurality of turbine blades in the circumferential direction of a rotor disk,
Data acquisition means for acquiring a rotor unbalance amount that is an unbalance amount of the rotor disk;
A plurality of the turbine blades are grouped by a predetermined number, and a blade set is formed by attaching the turbine blades in the same group to a support member having an unbalance amount of zero so that the turbine blades are equally spaced in an arbitrary arrangement. as the calculation means unbalance amount of the blade set respectively calculated, on the basis of the unbalanced weight of the rotor unbalance amount and the wings set, the rotor unbalance amount of the rotor disk is reduced And an arrangement device for arranging the blade set with respect to the rotor disk. 5. The turbine rotor blade arrangement device according to claim 4 , wherein in the calculation means, the plurality of turbine rotor blades are grouped in order of lighter or heavier based on the weight of each turbine rotor blade. In the arrangement means, to change the combination of the arrangement of the blades set, it calculates the unbalance amount of the turbine rotor in each case, according to claim 4 or claim identifies an arrangement in which the unbalance amount is minimum turbine blade arrangement according to 5. The turbine rotor blade arrangement device according to claim 4 , wherein the data acquisition unit measures a rotor unbalance amount based on the position of the eccentric gravity center and the eccentric gravity center amount. A turbine rotor blade arrangement program in a turbine rotor formed by mounting a plurality of turbine rotor blades in the circumferential direction of a rotor disk,
A first process for obtaining a rotor unbalance amount that is an unbalance amount of the rotor disk;
A plurality of the turbine blades are grouped by a predetermined number, and a blade set is formed by attaching the turbine blades in the same group to a support member having an unbalance amount of zero so that the turbine blades are equally spaced in an arbitrary arrangement. A second process for calculating the unbalance amount of each wing set;
On the basis of the unbalanced weight of the rotor unbalance amount and the wings set, so that the rotor unbalance amount of the rotor disk is reduced, a third process of placing the wings set against the rotor disk And a turbine blade arrangement program for causing a computer to execute.

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