JPS5958335A - Method and device for monitoring life of prime mover material - Google Patents

Abstract

PURPOSE:To detect the life of a prime mover material in advance, by obtaining the stress value of a separated material, comparing the stress value with the secular stress value of them aterial based on the operated times, etc., and obtaining the distribution of the creep life etc., of the materials. CONSTITUTION:A life monitoring device is constituted of a setter 1 which inputs various parameters necessary to calculate the accumulated amount of damage obtained from the operated history of a prime mover, fatigue failure calculator 2 which calculates the fatigue failure of the whole prime mover materials, creep failure calculator 3 which calculates the accumulated amount of creep faiure, display 4, and recorder 5. When the kind and frequency of unstationary operations and the kind and time of stationary operations are inputted into the setter 1, the distributing conditions of the accumulated amounts of the fatigue failure and creep failure of the whole prime mover materials are calculated by the calculators 2 and 3 and automatically displayed by the display 4 as numerical values or charts. Therefore, the damaged state of the materials can easily be known in advance.

Description

[Detailed Description of the Invention] [Technical Field of the Invention] The present invention-1 Original 711J+Iso, for example, knowing the expected life of a turbine member in advance (q) hl f! i! I Machine parts life monitoring method and device &, +-ITJ.

[Technical debt of invention and 111 points] Hara n+! +
A) is often used for 10 years or more, and those CJ lengths are in use for 1114 years (2 unsteady and 51 normal operation lpX, l'j!;j
do. During such operation, t, j, unsteady stress, and steady stress occur in the original IIIJ Isobe layer in the temperature field during each operation,
Undefined) 3゛J′I!・Reincarnation has 9M labor damage, and during steady operation, C2 has accumulated 4bh of creep TFI and 4bH since it is used in active condition. As the period of use of the original 11 increases, it accumulates, and when the limit damage characteristic value ζ of the material composing the original 1ldr 11 is combined, cracks occur in the prime mover section '4A. If the crack propagates within a short period of time, the life of the prime mover member will be determined shortly after the crack occurs (avgj, (2).

Therefore, it is essential to predict the state of damage to the motive force-like member ζ2 from the viewpoint of maintenance of the motive force.

[Purpose of the invention]

The present invention is based on the above-mentioned circumstances and provides a method and device for a prime mover section in which the expected life of a member is detected in advance.

In order to achieve the purpose of the present invention, the stress value of the divided member is determined, and the stress value of the member over time based on this value and the number of operations or duration of operation is calculated. This is to calculate the component 1i of the creep life of the member. In addition, in order to detect the lifespan of members in advance (2) a memory device, a kcs setting device, a fatigue and creep damage meter, and a device for displaying and recording calculation results are provided.

[Embodiments of the invention]

Prior to a detailed explanation of the present invention, its logical means will be explained in detail.

In general, there are many ways to express fatigue damage that can be accumulated per unsteady operation, or creep damage that can be accumulated per hour of steady operation, but the most common expression is 1 usage minute. The former is expressed by equation (1) and the latter by equation (2).

φ7L = ”-1-(1) N7L (T, σ) Here, NfL (T + σ) is the unsteady operation in the ox where the temperature T and stress σ that occur in the unsteady J transfer act, and cracks occur. The number of repetitions represents persimmons in unsteady operation.Tr
/(T, σ) is the temperature T that occurs during steady operation.

The steady-state operating time until a crack occurs due to the stress σ is applied, and / is the steady-state operating force ゛1. For convenience of explanation, we assume that each of the volatiles in unsteady operation and constant 'FS y' J = one class, and that the temperature is To and the stress is σ().
The chain operation occurs n 1ij1, the temperature is TQ', and the stress is 0.
Considering a prime mover whose steady operation time is 0' for one hour, the fatigue damage and creep damage kl accumulated in this prime mover can be determined by equations (1) and (2), respectively. Generally, the eight volumes of fatigue damage and creep damage are expressed in equations (3) and (4), respectively.

Φ' −”Iπ(0,o)−T n”φfL i8
1 Here, %rl''l is the number of occurrences of unsteady operation, and J is the duration of steady operation, respectively.

Therefore, when the equations (3) and (4) (f2) and the accumulation of fatigue damage and creep damage (h) reach their limit values, cracks occur. This limit damage value is 1
Jino & Labor, Creep (1+j1 depending on β wound accumulation status)
The value of each item is determined by the bribery fee. I
From the rolling history of the prime mover and the temperature and stress during operation, the accumulation of fatigue scratches and creep damage Kr "t fsi" Φf, Φ can be calculated using equation (8) or equation (41).
Φf and Φ. Φf, Φ can be defined by the limit damage value D (ΦI, Φ.) of the prime mover member determined by the matching of the parts. Φf, Φ within the coordinate system. That is a state in which no cracks have occurred in the original Xa + machine layer, and Φf, Φ. is D(r, r')f
, ΦC), it can be determined that the closer it is to crack initiation.

By the way, general C Nihara IIIJ (W4 is large T14
``It is a created thing'' 21 go is common, Hara! The temperature and stress during operation inside the tilt machine section 4J differ depending on the location. Therefore, Jti is the accumulation of wounds (7j')i; itself is the original! l
i! ＋＋j! It has a distribution within the A section. Therefore, it is safe to judge the health of the prime mover by knowing the scratches throughout the entire interior of the original Tabe phase, which is in a damaged state. By the way, the damaged state inside the prime mover in winter is clearly determined by the equations (1) and (2) in section 1, above, when the temperature and stress state of the heat transfer in that part are known. Temperature L ((, -, stress state (, tu 1. for the entire structure) temperature L(, -, stress state (, tu 1. for the entire structure) temperature 1'i!j, finite, 9.1' elemental method for analyzing stress state It is easier to know than C2.

In other words, the temperature gr of the entire prime mover divided into elements 1 and 1 of finite size, and the analysis result of stress distribution.
Since there is a clear number in the case of battered fish, the damage condition at the representative point 1) 11 is determined by Equation (1) and Equation (A) 2).
or t per hour of steady operation; Therefore, 41
You can know the state of damage accumulation.

2. A model realized based on the method of calculating the damage accumulation state of the entire prime mover components explained above! The life monitoring system fi, 'i- of the riII aircraft components will be explained below in total M11.

Figure 1 shows a 414 diagram of a life monitoring device for a driving member. 1 is a setting device, which calculates damages such as 4it+ type of unsteady operation and its number, knowledge of steady operation and its operating time, etc. from the driving history of the prime mover 2 is a storage device that records in advance the temperature inside the prime mover that occurs during raw materials, rigs, various unsteady operations, and steady operations.

By dividing the entire prime mover into finite elements, analyzing the stress using the finite element method, and comparing the results with the fatigue characteristics and creep-rubber characteristics of the prime mover components, the Fatigue damage and creep damage accumulated per hour of operation are calculated for the representative points of each finite element, and the total η results are stored together with the coordinates of the representative points. Again, come on! The critical damage value D (ΦhaΦ) corresponding to the occurrence of 7
. ) also has a poor memory. y, 3 labor injuries 1 injury on 14 ^I
Creep damage of I, 4, Ml force, Ml force (-, so it is stopped ()) and total force damage or d creep damage, 1: I, total 9
- I remember being depressed.

This is a 3-digit fatigue damage calculator, and the number and number of unsteady operations input from the iν constant device in 1, and the number of unsteady operations inputted from the iν constant device in 1. This is a device that calculates the accumulated amount of fatigue damage Φf from the fatigue damage caused by the collision, using equation (3) above.4 - Creep damage calculator, where f= of steady operation input from the setting device 1.
Jf type and its time, and the creep damage of the entire built-in structure after 1 hour of constant operation are determined by the creep damage accumulation Φ from the above equation (41) (2). This is a calculation device. 5 is a display that displays the results of fatigue damage, creep damage, Δ1:!J!, separately or in combination with the coordinates indicating the position quotient inside the prime mover. This is a device that graphically displays a creep damage diagram such as 1-1 flaws (Fig. 1) or a total 111 flaw diagram along with the outline of the prime mover parts in equal straight lines. Internal fatigue damage and creep (δ
4Φf, Φ for the accumulation of scratches. The combination of is the marginal damage D(Φf,
(po) is close to (3 minutes I/A, the element is
・is displayed blinking. 6 is a recorder, which records the essential parameters for the damage meter/R inputted from the setting device (1), the fatigue loss deflection device (2), the results of creep damage calculations (3), etc. It is a device.

〔Effect of the invention〕

As stated above in i), 5 two-skin excitation tfJ, the operator is 4
4!1 Unsteady operation revealed from the operation history of the engineer
Type 1 and its number.

Just by inputting the normality of steady operation and its time from the setting device 1, fatigue damage of the entire prime mover member, creep l - damage accumulation value of the prime mover f (13 months overall distribution yIJ, i), fatigue damage calculator 2 and creep damage H1 is calculated by calculator 3, automatically displayed numerically or graphically as an equal damage diagram on display i4, and recorded in recorder 5, so it is extremely easy to check the damage state of the prime mover. JV! It is now possible to grasp the JV! From this C2, it is possible to know in advance when to return the prime mover parts while operating the prime mover, and to update the parts or reduce the operating condition in a timely manner. The maintenance of the prime mover can be said to be extremely rewarding.

4 Explanatory diagram 1ii of 17+) is the Lifespan Monitor R5 published by Modo 4a by the present invention f2.
Edict.

This is a schematic diagram.

1... Setup 5 pin device 2... Transfer damage tear η- device 3... Creep JM injury Ml' calculator 4... Display device 5
・・・ h self recorder

Claims (1)

[Claims] (1) Divide the original aircraft wreck into two elements of finite size, find the actual measured value of stress at a representative part within the armpit, and calculate the stress of the member based on this measured value and the number of operations or duration. Comparing with the stress value within the year, the chestnut of part t (2) original Q
i, l) Divide the machine member into two parts of a finite size, and calculate the fatigue damage value accumulated per unsteady operation of the prime mover member at the representative part f2 within this element and the value accumulated per hour of W normal 111J rotation. a storage device 4 containing creep damage values, a setting device for setting the type and number of unsteady operation, the seed furnace for steady operation and its time, etc., and a storage device for fatigue damage and creep damage.
Calculate the amount of fatigue loss = i + 9 aircraft and creep damage total 7? A lifespan monitoring device for prime mover components, comprising a motor, a display that displays fatigue damage B1 calculation results and creep damage meter connection results in a concave shape or numerically, and a recorder that records the calculation results.