CN113513374B

CN113513374B - Conveniently detachable compressor stationary blade ring of ship gas turbine and assembling method thereof

Info

Publication number: CN113513374B
Application number: CN202110842609.3A
Authority: CN
Inventors: 邓庆锋; 孙勇; 吴迪; 高思华; 任兰学
Original assignee: 703th Research Institute of CSIC
Current assignee: 703th Research Institute of CSIC
Priority date: 2021-07-26
Filing date: 2021-07-26
Publication date: 2022-10-21
Anticipated expiration: 2041-07-26
Also published as: CN113513374A

Abstract

The invention belongs to the technical field of processing of a compressor stationary blade ring, and particularly relates to a conveniently detachable compressor stationary blade ring of a ship gas turbine and an assembling method thereof. The invention comprises a blade ring, a common stationary blade and two stationary blades with notches on the lower edge plates, wherein the blade ring comprises an outer ring and an inner ring, and a clamping groove is arranged on the whole inner ring; the blade ring is composed of two split half blade rings, and the split notch divides the clamping groove into two half clamping grooves. Firstly, respectively sliding the fixed blades with notches on the two lower edge plates into the half clamping grooves along the notches of the two split half blade rings to be matched with the stop blocks; then sequentially installing common stationary blades with complete upper and lower flange structures; and finally, splicing the two split half blade rings to form a complete stator blade ring. The invention has the advantages of flexible structure, convenient installation and disassembly, suitability for compressors with different structural forms and the like.

Description

Conveniently detachable compressor stationary blade ring of ship gas turbine and assembling method thereof

Technical Field

The invention belongs to the technical field of processing of a compressor stationary blade ring, and particularly relates to a conveniently detachable compressor stationary blade ring of a ship gas turbine and an assembling method thereof.

Background

The compressor is an important component of an aircraft engine, a ground or a ship gas turbine. A typical compressor is generally a multi-stage axial flow configuration, each stage consisting of a row of moving blades and a row of stationary blades. The compressor stator blade is used for gradually converting the power potential energy applied to airflow by the movable blade into pressure potential energy and guiding the airflow to the direction required by the inlet of the movable blade of the next stage. As is known, each of the compressor stator blades generally comprises an upper rim, a stator blade and a lower rim, which are assembled in turn, in use, on a compressor casing, forming an integral stator blade ring comprising a ring of stator blades and constituting, together with the rotor blade row, a compressor airflow path. The vane ring is therefore mounted in the compressor with strict position requirements and is able to prevent itself from moving in the circumferential, radial and axial directions. Usually, the upper edge plate of the compressor stator blade is connected with the outer ring or the casing in a tenon-mortise mode, and the lower edge plate is connected with the inner ring through riveting or welding. At present, the integral stator blade rings need to be matched with a semi-structure formed by circumferential cutting and are installed in a mode of being embedded into a compressor casing step by step. In order to meet the installation requirement, the compressor casing correspondingly adopts a half-split structure. In order to avoid circumferential movement of the stationary blade ring in the compressor casing, a bolt connection is required to be added to fix the stationary blade ring.

The stator blade ring has long processing period and high cost, and the compressor casing assembly with the structure has high manufacturing difficulty and needs higher part processing precision and matching precision. The assembly process is also very complicated, the number of parts is large, and a large amount of time is consumed. The assembly is difficult to disassemble after the assembly is finished, and only destructive decomposition can be adopted when disassembly is needed, so that great inconvenience is brought to maintenance.

Disclosure of Invention

The invention aims to provide a conveniently detachable compressor stationary blade ring of a ship gas turbine.

The purpose of the invention is realized by the following technical scheme: comprises a common stationary blade 1; the common stator blade 1 consists of an upper edge plate, a stator blade and a lower edge plate; the method is characterized in that: the device also comprises a blade ring and two stationary blades with notches on the lower edge plates; the blade ring comprises an outer ring and an inner ring 2, and a clamping groove is formed in the whole ring of the inner ring 2; the blade ring consists of two split half blade rings, and the split notch divides the clamping groove into two half clamping grooves; the two fixed blades with notches on the lower edge plates are respectively arranged at the end parts of the two split half blade rings, and the notches of the lower edge plates are connected with the half clamping grooves through the stop blocks 4; the common vane 1 is mounted at She Huanzhong.

The present invention may further comprise:

the front and rear sections of the outer ring of the blade ring are provided with grooves used for matching with the front and rear movable blade top outer ring stop pins 3.

The invention also aims to provide an assembling method of the conveniently detachable compressor stationary blade ring of the ship gas turbine.

The purpose of the invention is realized by the following technical scheme: the method comprises the following steps:

step 1: preparing two split type half-blade rings, a common stationary blade 1 and two stationary blades with notches on lower edge plates;

the split half blade rings can be spliced into a complete blade ring, the complete blade ring comprises an outer ring and an inner ring 2, a clamping groove is arranged on the whole inner ring 2, and the clamping groove is divided into two half clamping grooves by the split notches;

step 2: respectively installing the stop blocks 4 into the half clamping grooves of the two split half blade rings;

and step 3: sliding a stationary blade with a notch on the lower edge plate into the split notch of the split half-blade ring, and matching and positioning the notch of the lower edge plate with the stop block 4;

and 4, step 4: after the assembly of the two stationary blades with notches on the lower edge plates is completed, the common stationary blade 1 is installed in the two split type half blade rings;

and 5: and after all the stator blades are assembled, splicing the two split half blade rings into a complete stator blade ring.

The present invention may further comprise:

and (3) coating anti-wear lubricant on the matching surfaces of the common stator blade 1 and the stator blade and the inner ring 2, the two lower edge plates of which are provided with the notches.

The invention has the beneficial effects that:

the invention relates to a novel structural form for assembling a stationary blade ring of a gas compressor of a domestic ship gas turbine, which has the advantages of flexible structure, convenience in installation and disassembly, applicability to gas compressors of different structural forms and the like. The invention can also simplify the mechanism of the compressor casing, so that the compressor casing can integrally adopt a cylindrical structure, can be suitable for a high-pressure ratio compressor, and can better solve the horizontal split surface sealing problem of the compressor casing.

Drawings

Fig. 1 (a) is a schematic structural installation diagram of a compressor stationary blade ring which can be conveniently disassembled in a marine gas turbine.

Fig. 1 (b) is a C-C sectional view (normal vane) of fig. 1 (a).

Fig. 1 (C) is a cross-sectional view (a stationary blade having a notch in a lower edge plate) of fig. 1 (a) taken along line C-C.

FIG. 1 (d) is a cross-sectional view E-E of FIG. 1 (a).

FIG. 2 is a three-dimensional schematic diagram of a compressor stator blade ring of a marine gas turbine with easy disassembly according to the present invention.

Fig. 3 is a schematic view illustrating the installation of a compressor stationary blade ring and a compressor casing of a marine gas turbine according to the present invention.

Detailed Description

The invention is further described below with reference to the accompanying drawings.

The invention provides a conveniently detachable compressor stationary blade ring of a ship gas turbine, aiming at improving the assembly and maintenance of the compressor stationary blade ring and ensuring the safe, reliable and stable operation of the compressor stationary blade ring. The invention can be widely applied to the assembly process of the impeller machinery such as the gas compressor, the turbine, the steam turbine, the axial flow fan and the like.

The invention comprises a common stator blade 1, a blade ring, a first special stator blade 1-1 and a second special stator blade 1-2; the first special stationary blade 1-1 and the second special stationary blade 1-2 are stationary blades with notches on the lower edge plates, the notches are matched with the stop block 4, and the stop block 4 is installed in the clamping groove of the inner ring 2. The blade ring comprises an outer ring and an inner ring 2, and is composed of two split half blade rings, and the split notches divide the clamping groove into two half clamping grooves. And sliding a first special stationary blade 1-1 and a second special stationary blade 1-2 with notches on the lower edge plates into the half clamping grooves of the two split half blade rings along the horizontal split notches to be matched with the stop block 4. And then sequentially installing the stator blades 1 with complete upper and lower flange structures, and splicing the two split half-blade rings after all the stator blades slide into the two split half-blade rings to form the stator blade ring.

The mutual cooperation of the stop block 4 and the clamping groove of the inner ring 2 limits the relative circumferential movement among the common stator blade 1, the first special stator blade 1-1, the second special stator blade 1-2 and the inner ring 2.

Six grooves are respectively arranged in front of and behind the upper edge plate of the stationary blade ring, and are respectively matched and connected with the outer rings of the front movable blade and the rear movable blade through stop pins (3), so that the circumferential positioning of the stationary blade ring is realized. The static blade ring and the movable blade outer ring are arranged in the cylindrical casing, the static blade ring and the movable blade outer ring are of split structures, and the static blade ring and the movable blade outer ring are firstly arranged and then the cylindrical casing is arranged. After the static blade is damaged, only the damaged blade needs to be removed and reassembled, and the production efficiency is greatly improved.

Example 1:

the installation of a compressor vane ring of a gas turbine is described as an example. FIG. 1 (a) is a horizontal split vane ring with an inner ring structure. The full inner ring 2 is provided with a locking groove as shown in the cross-sectional view E-E in fig. 1 (d). The stop block 4 is firstly installed in the inner ring 2 along the direction of the clamping groove of the inner ring 2, then the first special stationary blade 1-1 and the second special stationary blade 1-2 which are installed in a matched mode with the stop block 4 and provided with notches on the lower edge plates slide into the T-shaped mortise along the split type notches, and then other complete common stationary blades 1 are installed. Each common stationary blade 1, the first special stationary blade 1-1 and the second special stationary blade 1-2 are fixed in the inner ring 2 through a T-shaped tenon-mortise structure. After all the blades are assembled, the two split stator blade rings are assembled together, namely, the relative motion among the common stator blade 1, the first special stator blade 1-1, the second special stator blade 1-2 and the inner ring 2 is limited. The final assembled three-dimensional view is shown in fig. 2. In the process of assembling the stationary blade ring, in order to avoid direct sliding friction between the lower edge plates of the common stationary blade 1, the first special stationary blade 1-1 and the second special stationary blade 1-2 and the inner ring 2, an anti-wear lubricant (material brand: letai 5104, the main component of which is molybdenum disulfide) can be smeared on the matching surfaces of the lower edge plates of the common stationary blade 1, the first special stationary blade 1-1 and the second special stationary blade 1-2 and the inner ring 2.

FIG. 3 is a schematic view of the installation of a compressor stationary blade ring and a compressor casing of a marine gas turbine with easy disassembly according to the present invention. Six grooves are arranged at the front section and the rear section of the upper edge plate of the stationary blade ring and are used for being matched with the outer ring stop pins 3 of the blade tops of the front movable blade and the rear movable blade. And each stage of stationary blade ring and each stage of movable blade outer ring are installed in a matching way through the stop pin 3 and the groove. The multi-section design is adopted for the static blade rings and the movable blade outer rings at all levels, so that the axial positioning of the static blade rings and the movable blade outer rings is realized, and the circumferential rotation effect between the static blade rings and the movable blade outer rings can be limited. Similarly, in order to effectively reduce the abrasion of the compressor casing in the assembling process of the stationary blade ring, an anti-wear lubricant can be coated on the matching surfaces of the stationary blade ring and the compressor casing.

The upper and lower edge plates of the common stationary blade 1, the first special stationary blade 1-1 and the second special stationary blade 1-2 and the inner ring 2 sliding groove are all of annular structures, and can be machined in a full-circle turning mode, so that the circumferential size consistency can be ensured, and the machining process is simplified. The inner ring 2 is provided with a circumferential sliding groove and is consistent with the tenon structures of the lower edge plates of the common static blade 1, the first special static blade 1-1 and the second special static blade 1-2, the common static blade 1, the first special static blade 1-1 and the second special static blade 1-2 can slide into the blade ring through the inner ring 2 horizontal split type notch, and each common static blade 1 can be independently installed and detached.

The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. A method for assembling a conveniently detachable compressor stationary blade ring of a ship gas turbine is characterized by comprising the following steps:

step 1: preparing two split type half-blade rings, a common stationary blade (1) and two stationary blades with notches on the lower edge plates;

the split half blade rings can be spliced into a complete blade ring, the complete blade ring comprises an outer ring and an inner ring (2), a clamping groove is formed in the whole inner ring (2), and the clamping groove is divided into two half clamping grooves by the split notches;

and 2, step: the stop blocks (4) are respectively arranged in the half clamping grooves of the two split half blade rings;

and step 3: sliding a stationary blade with a notch on the lower edge plate into the split type notch of the split type half-blade ring, and matching and positioning the notch of the lower edge plate with a stop block (4);

and 4, step 4: after the assembly of the two stationary blades with notches on the lower edge plates is finished, the common stationary blade (1) is installed in the two split type half blade rings;

2. The method for assembling a readily removable compressor vane ring for a marine gas turbine engine as claimed in claim 1, wherein: and (3) coating anti-wear lubricant on the matching surfaces of the common stator blade (1) and the stator blade and the inner ring (2) with notches on the two lower edge plates.

3. The method for assembling a compressor stationary blade ring of a marine gas turbine engine, which is easily disassembled, according to claim 1 or 2, wherein: the front section and the rear section of the outer ring of the blade ring are provided with grooves which are used for being matched with the stop pins (3) of the outer ring of the blade top of the front movable blade and the rear movable blade.