阅读说明：本技术 一种高温环境下工作的涡轮类型零件的加工方法 (Machining method for turbine type part working in high-temperature environment ) 是由 王岩 赵慧 于 2021-09-15 设计创作，主要内容包括：本发明公开了一种高温环境下工作的涡轮类型零件的加工方法,是在半精加工后通过常温状态下对每个叶片进行检测,再在高温状态下对每个叶片进行检测,可以得到叶片的失真值,将叶片的失真值换算成产品设计图纸尺寸的失真尺寸,再按反失真的设计图纸尺寸的失真尺寸对叶片进行精加工,这样叶片工作达到高温时将出现正失真,在高温状态下正、反失真相互抵消,使每个叶片在高温状态下,也就是工作温度下其坐标尺寸为叶片的图纸设计尺寸,完全保证了涡轮的工作性能和使用要求。完全解决了涡轮在高温下工作由于叶片不规则的变形而影响发动机的性能,从而使航天发动机达到世界领先水平。方法独特、实用性强、精准可靠、具有广泛的推广应用价值。(The invention discloses a method for processing turbine type parts working in a high-temperature environment, which is characterized in that after semi-finishing, each blade is detected in a normal-temperature state, then each blade is detected in a high-temperature state, the distortion value of each blade can be obtained, the distortion value of each blade is converted into the distortion size of the design drawing size of a product, and then the blades are subjected to finish machining according to the distortion size of the design drawing size of inverse distortion, so that the positive distortion occurs when the blades work at a high temperature, the positive distortion and the inverse distortion are mutually offset in the high-temperature state, the coordinate size of each blade in the high-temperature state, namely the working temperature is the design size of the blade, and the working performance and the use requirement of a turbine are completely ensured. The problem that the performance of the engine is affected due to the irregular deformation of the blades when the turbine works at high temperature is completely solved, so that the aerospace engine reaches the world leading level. The method is unique, strong in practicability, accurate and reliable, and has wide popularization and application values.)

1. A method for machining a turbine-type part operating in a high-temperature environment by measuring a deformation dimension at a high temperature and machining the turbine-type part in a reverse deformation dimension at room temperature, the method comprising the steps of: firstly, performing semi-finishing on each blade by reserving machining allowance of 0.5 +/-0.1 mm on a five-axis linkage numerical control machine tool according to the size of a turbine part, the size of a product and a product machining program; secondly, taking down the workpiece, and detecting the coordinate size of each blade one by using an optical scanner or a three-coordinate detector at room temperature and recording the coordinate size; thirdly, putting the workpiece into a high-temperature heating furnace, heating to 1000 +/-50 ℃, and preserving heat for 2.5 +/-0.5 hours; taking out quickly, detecting the coordinate size of each blade one by one quickly and recording the coordinate size; comparing the high-temperature measurement value of each blade with the room-temperature measurement value, wherein the positive error or negative error change can be obtained from each measurement value, the positive error and the negative error are called distortion, and the coordinate size of each blade after distortion can be further obtained; sixthly, obtaining the coordinate size of the reverse distortion of the semi-finished blade through the coordinate size of the distorted blade; seventhly, converting the coordinate size of the reverse distortion of each blade after semi-finishing to obtain the coordinate size of the reverse distortion of an actual product; inputting the actual coordinate size of each blade with reverse distortion into a five-axis linkage numerical control machine tool one by one, and performing finish machining according to the reverse distortion coordinate size of the actual coordinate size of the product; unloading the workpiece, and measuring according to the inverse distortion coordinate size of the actual product coordinate size; tenthly, after the workpiece is qualified, putting the workpiece into the high-temperature furnace again to generate the temperature to 1000 +/-50 ℃, and keeping the temperature for 2.5 +/-0.5 hours for heating; quickly taking out, and quickly detecting the coordinate size of each blade one by one again, wherein all the blades meet the design requirements of product drawings and are qualified products; and twelfth, naturally cooling, boxing and warehousing.

Technical Field

The invention relates to a machining method, in particular to a machining method for a turbine type part working in a high-temperature environment, and belongs to the technical field of aerospace industry.

Background

The turbine is a rotary power machine which converts the energy of a flowing working medium into mechanical work, and is one of the main parts of a gas turbine, a steam turbine and an aircraft engine. With the development of the industry, the navigation, aviation, aerospace and military industries are also rapidly developed, and the turbine is a key part related to the efficiency, noise and service life of an engine. The turbine is formed by connecting a conical rotating body with a central hole and a plurality of spiral blades which are symmetrically distributed, the requirements on the size consistency and the processing precision of the blades are high, the thin wall shape of the blades is complex and the processing difficulty is high, the original processing method is to process the conical rotating body and the blades respectively, weld the conical rotating body and the blades by plasma combination and polish the blades for forming, the quality of the processing method is difficult to ensure, the processing method is generally for civil use, and has a large distance from the wide application of navigation, aviation and aerospace, the prior art gradually develops to adopt a five-axis linkage numerical control machine tool to clamp and directly process a cylindrical material once, although the cylindrical material is processed and formed once, the utilization rate of the material is low, the service performance and the technical effect are greatly improved, the product quality is nearly in a perfect state, the military effect is achieved from civil use, and the aerospace industry is widely applied, in particular, the aerospace industry has been developed suddenly and suddenly. The existing five-axis linkage numerical control machine tool is a most advanced world processing method for directly processing and molding a cylindrical material at one time, and can be completely applied to an aerospace engine, but the turbine applied to high-speed rotation working in a high-temperature environment still has the practical conditions of unsatisfactory dynamic balance, high rotation noise and low working efficiency, the improvement and development of the overall performance of an aerospace vehicle are influenced, the processing method of the turbine must be further improved, the processing precision of the turbine is improved, the dynamic balance index of the turbine working in the high-temperature environment is improved, the service performance and the technical effect of the turbine in the high-temperature environment are improved, the efficiency of the aircraft is further improved, and the aircraft reaches the world leading level, which is a practical problem to be solved at present.

Disclosure of Invention

The invention aims to provide a method for machining a turbine type part working in a high-temperature environment. The turbine blade can be completely applied to a general aerospace engine, but can be applied to an aerospace engine working in a high-temperature environment, the blade of the turbine can be irregularly deformed due to complex shape and thin wall, the original dynamic balance index is changed to a certain extent, and the flight efficiency is greatly influenced, namely the coordinate size of the blade on the turbine is distorted in the comparison size between the high-temperature state and the normal-temperature state. The starting point of the invention is that the problem of distortion of the size of the blade can be satisfactorily solved by adopting an anti-distortion processing method to counteract the distortion. The specific processing method comprises performing semi-finishing with a certain amount of processing, detecting the coordinate size of each blade with an optical scanner or a three-coordinate detector at room temperature, heating the workpiece in a high temperature furnace, detecting the coordinate size of each blade under the high temperature state, comparing the high temperature measurement value with the room temperature measurement value, obtaining positive error or negative error change of each measurement point of each blade, and calling the positive error and the negative error as size distortion, and then the coordinate size after the distortion of the blade can be obtained, the actual reverse distortion coordinate size of each blade can be obtained through conversion, the actual coordinate size of the reverse distortion of the blade is input into a five-axis linkage numerical control machine tool, the blade with the actual reverse distortion coordinate size is subjected to finish machining, a workpiece subjected to finish machining is heated, the blade is detected again at high temperature according to the drawing requirements, and the qualified blade is stored in a warehouse for standby. The principle is as follows: after semi-finishing, each blade is detected at normal temperature, and then each blade is detected at high temperature, so that the distortion value of each blade can be obtained, the distortion value of each blade is converted into the distortion size of the design drawing size of a product, and then the blades are finished according to the distortion size of the design drawing size of inverse distortion.

The technical scheme adopted by the invention for solving the technical problems is as follows: a method for processing turbine type parts working in high-temperature environment is a method for processing the turbine type parts according to the reversible deformation size at room temperature by measuring the deformation size at high temperature, and comprises the following specific steps: firstly, performing semi-finishing on each blade by reserving machining allowance of 0.5 +/-0.1 mm on a five-axis linkage numerical control machine tool according to the size of a turbine part, the size of a product and a product machining program; secondly, taking down the workpiece, and detecting the coordinate size of each blade one by using an optical scanner or a three-coordinate detector at room temperature and recording the coordinate size; thirdly, putting the workpiece into a high-temperature heating furnace, heating to 1000 +/-50 ℃, and preserving heat for 2.5 +/-0.5 hours; taking out quickly, detecting the coordinate size of each blade one by one quickly and recording the coordinate size; comparing the high-temperature measurement value of each blade with the room-temperature measurement value, wherein the positive error or negative error change can be obtained from each measurement value, the positive error and the negative error are called distortion, and the coordinate size of each blade after distortion can be further obtained; sixthly, obtaining the coordinate size of the reverse distortion of the semi-finished blade through the coordinate size of the distorted blade; seventhly, converting the coordinate size of the reverse distortion of each blade after semi-finishing to obtain the coordinate size of the reverse distortion of an actual product; inputting the actual coordinate size of each blade with reverse distortion into a five-axis linkage numerical control machine tool one by one, and performing finish machining according to the reverse distortion coordinate size of the actual coordinate size of the product; unloading the workpiece, and measuring according to the inverse distortion coordinate size of the actual product coordinate size; tenthly, after the workpiece is qualified, putting the workpiece into the high-temperature furnace again to generate the temperature to 1000 +/-50 ℃, and keeping the temperature for 2.5 +/-0.5 hours for heating; quickly taking out, and quickly detecting the coordinate size of each blade one by one again, wherein all the blades meet the design requirements of product drawings and are qualified products; and twelfth, naturally cooling, boxing and warehousing.

The invention has the beneficial effects that: on an aerospace engine working in a high-temperature environment, blades of a turbine are irregular in deformation due to complex shapes and thin walls, the original dynamic balance index is changed to a certain degree, and therefore flight efficiency is greatly influenced. The method is unique, strong in practicability, accurate and reliable, and has wide popularization and application values.

Drawings

The invention is further described with reference to the following figures and detailed description.

FIG. 1 is a schematic view of the construction of a turbine type part of the present invention.

Fig. 2 is a schematic top view of the structure of fig. 1.

Fig. 3 is a schematic view of the conical rotary body of fig. 1.

Reference numerals

1. Conical rotator 2, blade 3, centre hole.

Detailed Description

Referring to fig. 1 to 3, a method for machining a turbine type part operating in a high temperature environment by measuring a deformation dimension at a high temperature and machining the turbine type part in a reverse deformation dimension at room temperature includes: firstly, performing semi-finishing on each blade by reserving machining allowance of 0.5mm on a five-axis linkage numerical control machine tool according to the size of a turbine part, the size of a product and a product machining program; secondly, taking down the workpiece, and detecting the coordinate size of each blade one by using an optical scanner or a three-coordinate detector at room temperature and recording the coordinate size; thirdly, putting the workpiece into a high-temperature heating furnace, heating to 1000 ℃, and preserving heat for 2.5 hours; taking out quickly, detecting the coordinate size of each blade one by one quickly and recording the coordinate size; comparing the high-temperature measurement value of each blade with the room-temperature measurement value, wherein the positive error or negative error change can be obtained from each measurement value, the positive error and the negative error are called distortion, and the coordinate size of each blade after distortion can be further obtained; sixthly, obtaining the coordinate size of the reverse distortion of the semi-finished blade through the coordinate size of the distorted blade; seventhly, converting the coordinate size of the reverse distortion of each blade after semi-finishing to obtain the coordinate size of the reverse distortion of an actual product; inputting the actual coordinate size of each blade with reverse distortion into a five-axis linkage numerical control machine tool one by one, and performing finish machining according to the reverse distortion coordinate size of the actual coordinate size of the product; unloading the workpiece, and measuring according to the inverse distortion coordinate size of the actual product coordinate size; tenthly, after the workpiece is qualified, putting the workpiece into the high-temperature furnace again to generate the temperature to 1000 ℃, and keeping the temperature for 2.5 hours for heating; quickly taking out, and quickly detecting the coordinate size of each blade one by one again, wherein all the blades meet the design requirements of product drawings and are qualified products; and twelfth, naturally cooling, boxing and warehousing.

Description of related Art: 1, determining the temperature of the high-temperature heating furnace according to the actual working temperature of the turbine. 2, the sizes of all the blades on the semi-finish machining turbine are the same, and the sizes are designed for the drawing with allowance. The sizes of all the blades on the turbine after finish machining are different, but when the turbine works at a determined high temperature, the sizes of all the blades are completely the same and designed for drawings, so that the high-quality stable work of the turbine is ensured, and the turbine produced and machined by the method of the invention completely reaches the world leading level.