CN-122007816-A - Machining and assembling method for stator blade ring combination of gas turbine

CN122007816ACN 122007816 ACN122007816 ACN 122007816ACN-122007816-A

Abstract

The invention discloses a processing and assembling method of a stator blade ring combination of a gas turbine, relates to a processing and assembling method of a stator blade ring, and is suitable for the field of stator blade ring assembling. The invention aims to solve the problems that in the prior art, when a stator blade ring of a gas turbine is assembled, the joggling and matching precision of a plurality of stator blades and an inner ring and an outer ring is difficult to control, the assembly stress is too large, the deformation of parts is easy to cause, and the reliable fixing of blades is difficult to realize; the method comprises the steps of fixing an outer ring on a mould for pouring low-melting-point alloy, pouring, and processing stator blade tongues, inserting the stator blade tongues on an inner ring and the outer ring, hot riveting the stator blade tongues, conveying the assembled outer ring, inner ring and stator blade into a heat treatment furnace, and finishing processing and assembling of a stator blade ring combination of a gas turbine.

Inventors

YAN JIANAN
LI YONGJIE
ZHANG XU
CHEN GUOHONG

Assignees

哈尔滨汽轮机厂有限责任公司
哈电发电设备国家工程研究中心有限公司

Dates

Publication Date: 20260512
Application Date: 20260319

Claims (9)

1. A processing and assembling method of a stator blade ring combination of a gas turbine is characterized by comprising the following steps: the first step is pre-assembling, wherein the outer ring is installed on an assembling clamp, and the tenon of the stator blade is installed on the outer ring; fixing an outer ring provided with the stationary blade on a mould for pouring low-melting-point alloy, compacting and fixing, pouring, and processing a stationary blade tongue provided with an inner ring; Step three, assembling, namely inserting the processed stator blade tongues on the inner ring and the outer ring, and carrying out hot riveting fixation on the stator blade tongues and the inner ring; stress relief, namely feeding the assembled outer ring, inner ring and stationary blade into a heat treatment furnace for stress relief treatment; and fifthly, dismantling the mould to finish machining and assembling of the stator blade ring combination of the gas turbine.
2. The method for machining and assembling a stator vane ring assembly of a gas turbine of claim 1, wherein said method is implemented by: In the first step, stator blade tenons are arranged in dovetail grooves corresponding to the outer ring, and the top and bottom surfaces of each stator blade are detected and polished, so that the relative positions of the stator blade tenons and the conical surface of the inner hole of the outer ring meet the requirement of a preset concave amount, and the fit clearance between the top of each stator blade and the dovetail groove of the outer ring is ensured.
3. The method for machining and assembling a stator vane ring assembly of a gas turbine of claim 1, wherein said method is implemented by: And in the second step, the stator blades with the tongues processed are removed on the casting piece and the outer ring, the stator blades are sequentially installed on the inner ring, and then a plurality of stator blades are installed on the outer ring in a sliding manner, so that the outer ring, the inner ring and the stator blades are assembled.
4. The method for machining and assembling the stator blade ring combination of the gas turbine, as set forth in claim 1, is characterized in that two end surfaces of the assembled outer ring are fixed on a vice, cold punching and riveting traces of the blade tongue are positioned after heating, oxyacetylene flame heating is carried out on the tongue protruding from the inner ring, then a punch is used for riveting the cold punching and riveting traces of the heating tongue, plastic deformation and flanging are carried out on the tongue, and therefore stator blades, the outer ring and the inner ring are fixedly connected into a whole.
5. The method for machining and assembling a stator blade ring assembly of a gas turbine according to claim 1, wherein turning is performed on two end surfaces of an outer ring after stator blade tenoning.
6. The method of assembling a stator vane ring assembly for a gas turbine according to claim 1, wherein the outer ring, the inner ring and the stator vanes are assembled and mounted on a tempering mold while stress is relieved, and the outer ring, the inner ring, the stator vanes and the tempering mold are fed into a heat treatment furnace for stress relief tempering.
7. The method for machining and assembling the stator blade ring combination of the gas turbine, according to claim 2, is characterized in that in the first step, a gauge is used for detecting the gap between the top and bottom surfaces of each stator blade and the dovetail groove, the gap is controlled to be between 0.02mm and 0.04mm by manually grinding the top and bottom surfaces of each stator blade, a depth gauge is used for checking and grinding, the concave amount of the end part of the blade root relative to the outer ring is ensured to be less than or equal to 0.3mm, and each blade is assembled and assembled, namely, a steel seal number is printed on the matched part of the side surface of the tongue and the dovetail groove of the outer ring.
8. The method for assembling a stator vane ring assembly for a gas turbine according to claim 3 and 7, wherein the stator vanes are sequentially installed on the inner ring, and then the stator vanes are correspondingly and slidably installed on the dovetail grooves of the outer ring according to the embossed seal numbers on the sides of the tongue.
9. The processing and assembling method for the stator blade ring combination of the gas turbine, according to claim 4, is characterized in that when oxyacetylene flame heating is carried out on the tongue protruding from the inner ring, an infrared temperature measuring gun is used for monitoring the temperature, when the temperature reaches 1000 ℃, a single-side hot riveting punch is used for riveting, rapid hammering is carried out in the riveting stage for preliminary shaping, the shape is trimmed by tapping, and finally the depth of the formed rivet is 1.2mm and the width is 2.8mm.

Description

Machining and assembling method for stator blade ring combination of gas turbine Technical Field The invention relates to a stator blade ring machining and assembling method, in particular to a machining and assembling method for a stator blade ring combination of a gas turbine, which is suitable for the field of stator blade ring assembling. Background The small industrial gas turbine is used as core power equipment of the distributed energy system, and has wide application prospect in the power generation field by virtue of the advantages of high efficiency, flexibility and environmental protection, and the running performance of the small industrial gas turbine directly determines the power supply stability and the energy utilization efficiency of the distributed energy system. The stator blade ring is used as a core stator component of the gas turbine compressor, and has the core function of guiding high-speed airflow thrown out by the movable blade into the next-stage movable blade according to the optimal pneumatic angle, so that the efficient conversion from the kinetic energy of the airflow to the pressure energy is realized, the structural precision and the assembly quality of the stator blade ring directly influence the compression efficiency and the operation stability of the compressor, and the overall working performance and the service life of the gas turbine are further determined. At present, an inner ring and outer ring assembly type structure is generally adopted for a stator blade ring of a gas turbine, and in the assembly process, a plurality of stator blades which are independently processed are fixed in mortises of an inner ring and an outer ring correspondingly through tenon, tongue and other mortises, so that a complete annular component is formed by assembly, and the pneumatic performance and structural strength requirements of the gas turbine during operation are met. However, in the prior art, the processing and the assembling process of the stator blade ring of the gas turbine are mutually independent, and lack of cooperative design and control, so that a plurality of technical problems exist in the assembling process, and the assembling precision, the structural stability and the use reliability of the stator blade ring are seriously affected; secondly, the integral assembling stress is overlarge in the assembling process, larger external force is required to be applied to realize the matching of the stator blade and the inner ring and the outer ring in the assembling process due to insufficient joggling matching precision, so that the integral assembling stress of the stator blade ring is caused, the defects of part deformation, cracks and the like are easily caused in the long-term service process, the service life of the stator blade ring is influenced, thirdly, the reliable fixing of the stator blade is difficult to realize while the joggling high-precision matching is ensured, in the existing assembling mode, contradiction exists between the high-precision matching and the reliable fixing, if the matching precision is excessively pursued, the stator blade is easy to loose after the stator blade is assembled, the air flow impact force and the vibration load of the gas turbine in the working process can not be borne, and if the fixing reliability is excessively emphasized, the assembling stress is further increased, and the deformation risk of the part is increased. Disclosure of Invention The invention aims to solve the problems that in the prior art, when a stator blade ring of a gas turbine is assembled, the joggling and matching precision of a plurality of stator blades and an inner ring and an outer ring is difficult to control, the assembly stress is too large, the deformation of parts is easy to cause, and the reliable fixing of blades is difficult to realize, and further provides a processing and assembling method for the stator blade ring combination of the gas turbine. The application adopts the following technical scheme for solving the problems: a processing and assembling method of a stator blade ring combination of a gas turbine is realized according to the following steps: the first step is pre-assembling, wherein the outer ring is installed on an assembling clamp, and the tenon of the stator blade is installed on the outer ring; fixing an outer ring provided with the stationary blade on a mould for pouring low-melting-point alloy, compacting and fixing, pouring, and processing a stationary blade tongue provided with an inner ring; Step three, assembling, namely inserting the processed stator blade tongues on the inner ring and the outer ring, and carrying out hot riveting fixation on the stator blade tongues and the inner ring; stress relief, namely feeding the assembled outer ring, inner ring and stationary blade into a heat treatment furnace for stress relief treatment; and fifthly, dismantling the mould to finish machining and assembling of the stator blade