Online dynamic balance measuring system for gas turbine rotor

Abstract

The utility model discloses an on-line dynamic balance measuring system for a gas turbine rotor, and the system comprises a gas compressor housing which is internally provided with a gas compressor blade; one side of the combustion chamber shell is connected with the gas compressor shell, the gas compressor blades and the turbine power blades are arranged in the shell, the corresponding shell is detached according to the positions where the blades need to be replaced, the rotor is rotated to a proper angle through a turning mechanism of the gas turbine, and the blades are sequentially detached and replaced with new blades; the balancing weight mounting opening is formed in the side wall of the combustion chamber shell; the exhaust chamber is connected with the other side of the combustion chamber shell; the measuring system module adopts a man-machine interaction system of a gas turbine generator set, solves the problem that the residual unbalance amount of a rotor is out of tolerance after blades of a gas turbine are replaced, and reduces the processes of large decomposition of the gas turbine, disassembly of a housing, disassembly of related complete systems, long-distance transportation of the rotor, reassembly and the like.

Description

Technical Field

[0001] The utility model relates to the technical field of dynamic balancing of gas turbines, and specifically relates to an online dynamic balancing measurement system for a gas turbine rotor. Background Art

[0002] Among the related technologies, the field of thermal power generation has a long history of development and provides sufficient energy for the development of the world economy. As a new power generation mode, gas turbines have the advantages of fast start and stop, high efficiency, less pollution and small footprint. During the long-term operation of gas turbines in power plants, it is inevitable that blade wear, damage and falling of blades, and blade coating shedding will exceed the operating requirements. In order to ensure the stable operation of the unit, the rotor blades must be replaced.

[0003] In the process of implementing the embodiments of the present disclosure, it is found that there are at least the following problems in the related art:

[0004] The quality of the newly replaced blades has changed compared to the original blades. In order to prevent the engine from shutting down due to excessive vibration during operation, the repaired engine rotor needs to be dynamically balanced. At present, the dynamic balancing method for gas turbine rotors after blade replacement is to disassemble the engine and transport the rotor to a professional manufacturer for dynamic balancing. This not only requires a large workload and a long cycle, but also there is a certain risk during long-distance transportation of the rotor, which in turn causes great economic losses. Utility Model Content

[0005] The utility model aims to provide an online dynamic balancing measurement system for a gas turbine rotor to solve the problems raised in the above-mentioned background technology.

[0006] To achieve the above-mentioned purpose, the utility model provides the following technical solutions: an online dynamic balancing measurement system for a gas turbine rotor, comprising: a compressor casing, in which compressor blades are arranged; a combustion chamber casing, one side of which is connected to the compressor casing, in which the compressor blades and turbine power blades are arranged, and the corresponding casing is removed according to the need to replace the blade position, and the rotor is turned to an appropriate angle by using the cranking mechanism of the gas turbine, and the new blades are removed and replaced in sequence; a counterweight installation port is arranged on the side wall of the combustion chamber casing; an exhaust chamber is connected to the other side of the combustion chamber casing; and a measurement system module adopts the human-computer interaction system of the gas turbine generator set itself.

[0007] Preferably, the compressor blades in the compressor casing are 1-6 level compressor blades.

[0008] Preferably, the compressor blades in the combustion chamber casing are 7-13 level compressor blades.

[0009] Preferably, the turbine power blades are two-stage or three-stage turbine power blades.

[0010] Preferably, the measurement system module includes a rear bearing vibration sensor, a front bearing vibration sensor, a speed sensor and an angle phase sensor, the front bearing vibration sensor, the speed sensor and the angle phase sensor are all arranged on one side of the compressor casing, and the rear bearing vibration sensor is arranged on one side of the combustion chamber casing.

[0011] Preferably, it also includes:

[0012] The counterweight installation groove is arranged in the groove on the front side of the first-stage compressor wheel of the gas turbine rotor and on the rear side of the last-stage compressor wheel;

[0013] The wheel disc counterweight installation groove is arranged in the shell of the combustion chamber shell.

[0014] Compared with the prior art, the utility model has the following beneficial effects: the utility model only needs to dismantle the compressor and the upper cylinder of the turbine where the blades need to be replaced, and then directly carry out the blade replacement operation, without the need to dismantle the gas turbine generator set, such as the cover, the entire cylinder of the gas turbine, the related complete system, etc., as well as the operations of hoisting and transporting the rotor. After the blades are replaced, the upper cylinder of the blade part can be reinstalled, and the online dynamic balancing operation can be directly carried out, which greatly improves the work efficiency and safety, avoids unnecessary waste in economy and cycle, saves a lot of maintenance costs, solves the problem of excessive residual imbalance of the rotor after the gas turbine blades are replaced, and reduces the processes of large-scale disassembly of the gas turbine, dismantling of the cover, dismantling of the related complete system, long-distance transportation of the rotor and reinstallation. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 It is a schematic diagram of the external structure of the utility model;

[0016] Figure 2 This is a schematic diagram of blade installation of the utility model;

[0017] Figure 3 This is a schematic diagram of the measurement system principle of the utility model.

[0018] In the figure: 1. Compressor casing; 2. Combustion chamber casing; 3. Counterweight installation port; 4. Exhaust chamber; 5. Compressor blades; 6. Turbine power blades; 7. Measurement system module; 7-1. Rear bearing vibration sensor; 7-2. Front bearing vibration sensor; 7-3. Speed ​​sensor; 7-4. Angle phase sensor. DETAILED DESCRIPTION

[0019] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.

[0020] See also Figure 1-3 The utility model provides a technical solution: an online dynamic balancing measurement system for a gas turbine rotor, comprising a compressor casing 1, a combustion chamber casing 2, a counterweight installation port 3, an exhaust chamber 4 and a measurement system module 7, wherein the casing 1 is provided with a compressor blade 5; one side of the combustion chamber casing 2 is connected to the compressor casing 1, wherein the casing is provided with a compressor blade 5 and a turbine power blade 6, and the corresponding casing is removed when the blade position is changed as required, and the rotor is turned to an appropriate angle by using the cranking mechanism of the combustion engine, and the blades are removed and replaced in sequence; the counterweight installation port 3 is arranged on the side wall of the combustion chamber casing 2; the exhaust chamber 4 is connected to the other side of the combustion chamber casing 2; the measurement system module 7 adopts the human-computer interaction system of the gas turbine generator set itself, and the corresponding casing is removed when the blade position is changed as required, and the rotor is turned to an appropriate angle by using the cranking mechanism of the combustion engine, and the blades are removed and replaced in sequence.

[0021] Specifically, the compressor blades 5 in the compressor housing 1 are 1-6 level compressor blades. The compressor is a component in a gas turbine engine that uses high-speed rotating blades to work on the air to increase the air pressure. The front end portion of the compressor impeller blade is curved and is called a guide wheel. Its function is to guide the gas into the working impeller without impact and reduce the impact loss of the airflow. The compressor impeller of a small supercharger generally integrates the guide wheel and the working impeller. There is a diffuser at the impeller outlet of the compressor to convert the kinetic energy obtained by the gas in the impeller into pressure as much as possible. The diffuser is divided into two types: blade type and slot type. The outer casing of the compressor has an airflow inlet and outlet. The inlet is generally arranged axially and the flow channel is slightly tapered to reduce the intake resistance. The outlet is generally designed to be a volute with a flow channel gradually expanding along the circumference, so that the high-speed airflow continues to be expanded there, thereby improving the overall efficiency of the supercharger. The compressor is driven by a turbine, and its main performance parameters include speed, flow, air flow, compression ratio and efficiency.

[0022] Specifically, the compressor blades 5 in the combustion chamber casing 2 are 7-13 level compressor blades. The corresponding casing is removed according to the need to replace the blade position, and the rotor is turned to the appropriate angle using the cranking mechanism of the engine, and the blades are removed and replaced with new ones in sequence.

[0023] Specifically, the turbine power blades 6 are two-stage or three-stage turbine power blades. Turbine blades are important components of turbine machinery, such as steam turbines, gas turbines, water turbines, etc., used to guide the fluid to flow in a certain direction and drive the rotor to rotate. The blades installed on the casing are called stationary blades or guide vanes, and the blades installed on the rotor are called moving blades. The main body of the turbine blades is the blade body, and its size is related to the flow capacity of the turbine.

[0024] Specifically, the measurement system module 7 includes a rear bearing vibration sensor 7-1, a front bearing vibration sensor 7-2, a speed sensor 7-3 and an angle phase sensor 7-4. The front bearing vibration sensor 7-2, the speed sensor 7-3 and the angle phase sensor 7-4 are all arranged on one side of the compressor casing 1, and the rear bearing vibration sensor 7-1 is arranged on one side of the combustion chamber casing 2.

[0025] Specifically, it also includes a counterweight installation groove 8 and a wheel counterweight installation groove 9. The counterweight installation groove 8 is arranged in the front groove of the first-stage compressor wheel of the fuel turbine rotor and the rear side of the last-stage compressor wheel; the wheel counterweight installation groove 9 is arranged in the shell of the combustion chamber shell 2.

[0026] Turn the gas turbine to the range of 500-700rmp; measure the low-speed unbalance of the unit through the measurement system module 7, and shut down after the measurement; install the specified counterweight in the counterweight installation slot 8, with a given angle and counterweight mass. Restart the gas turbine rotor and repeat the measurement until it is qualified; after the low-speed dynamic balance is qualified, reinstall the shell removed from the gas turbine; start the gas turbine again, increase the speed to full speed in a gradient of 500rmp, and measure the dynamic balance of each different speed gradient; install the counterweight of the specified mass according to the preset counterweight scheme, until the dynamic balance given by the measurement system meets the design range when the gas turbine is turned to full speed.

[0027] Working principle: When the utility model is working, the compressor blades 5 in the compressor casing 1 are 1-6 level compressor blades, and the compressor blades 5 in the combustion chamber casing 2 are 7-13 level compressor blades. The blade position is replaced as needed and the corresponding casing is removed. The compressor and turbine upper cylinder of the gas turbine are removed, and the rotor is turned to a suitable angle by using the turning mechanism to replace the damaged working blades. The rotor is turned to 500-700rmp by starting the system, and the unbalance of the rotor is detected by the dynamic balancing measurement system. According to the measured data, a counterweight of suitable mass is installed at a specified angle at the position of the rotor unbalance adjustment installation hole / slot reserved for the rotor according to the measured data, and the rotor is increased to a slow speed according to different gradients, and the dynamic balance of the rotor is repeatedly measured. The position and mass of the counterweight to be installed are optimized according to the measured data, so that the rotor unbalance meets the design requirements.

[0028] In the description of the present invention, unless otherwise clearly specified and limited, the terms "installed", "connected", "connected", and "fixed" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0029] The standard parts used in the utility model can all be purchased from the market, and special-shaped parts can be customized according to the instructions and the drawings. The specific connection methods of each part adopt the conventional means such as mature bolts, rivets, welding, etc. in the existing technology. The machinery, parts and equipment all adopt the conventional models in the existing technology, and the circuit connection adopts the conventional connection method in the existing technology, which will not be described in detail here.

[0030] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A gas turbine rotor online dynamic balancing measurement system, characterized in that: include: A compressor casing (1), wherein compressor blades (5) are arranged in the casing (1); A combustion chamber casing (2) is connected to the compressor casing (1) at one side thereof. The compressor blades (5) and turbine power blades (6) are arranged in the casing. When the blade positions are changed as required, the corresponding casing is removed. The rotor is rotated to an appropriate angle using the cranking mechanism of the combustion engine, and the blades are removed and replaced in sequence. A counterweight installation opening (3) is provided on the side wall of the combustion chamber shell (2); An exhaust chamber (4) connected to the other side of the combustion chamber shell (2); The measurement system module (7) uses the human-machine interaction system of the gas turbine generator set itself.

2. The gas turbine rotor online dynamic balancing measurement system according to claim 1, characterized in that: The compressor blades (5) in the compressor casing (1) are 1-6 level compressor blades.

3. The gas turbine rotor online dynamic balancing measurement system according to claim 1, characterized in that: The compressor blades (5) in the combustion chamber casing (2) are 7-13 level compressor blades.

4. The gas turbine rotor online dynamic balancing measurement system according to claim 1, characterized in that: The turbine power blades (6) are two-stage or three-stage turbine power blades.

5. The gas turbine rotor online dynamic balancing measurement system according to claim 1, characterized in that: The measurement system module (7) comprises a rear bearing vibration sensor (7-1), a front bearing vibration sensor (7-2), a rotation speed sensor (7-3) and an angle phase sensor (7-4); the front bearing vibration sensor (7-2), the rotation speed sensor (7-3) and the angle phase sensor (7-4) are all arranged on one side of the compressor casing (1), and the rear bearing vibration sensor (7-1) is arranged on one side of the combustion chamber casing (2).

6. The gas turbine rotor online dynamic balancing measurement system according to claim 1, characterized in that: Also includes: The counterweight installation groove (8) is arranged in the groove on the front side of the first-stage compressor wheel disc of the combustion engine rotor and on the rear side of the last-stage compressor wheel disc; The wheel disc counterweight installation groove (9) is arranged in the shell of the combustion chamber shell (2).

Images