CN115060404A - Axial force testing device - Google Patents

Axial force testing device Download PDF

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Publication number
CN115060404A
CN115060404A CN202210770169.XA CN202210770169A CN115060404A CN 115060404 A CN115060404 A CN 115060404A CN 202210770169 A CN202210770169 A CN 202210770169A CN 115060404 A CN115060404 A CN 115060404A
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CN
China
Prior art keywords
thrust bearing
axial force
mounting
air
testing device
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
CN202210770169.XA
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Chinese (zh)
Inventor
李乃宇
李成勤
钟猷兰
顾明恒
韩孟克
董诗国
叶馨怡
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Enn Energy Power Technology Shanghai Co ltd
Original Assignee
Enn Energy Power Technology Shanghai Co ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Enn Energy Power Technology Shanghai Co ltd filed Critical Enn Energy Power Technology Shanghai Co ltd
Priority to CN202210770169.XA priority Critical patent/CN115060404A/en
Publication of CN115060404A publication Critical patent/CN115060404A/en
Pending legal-status Critical Current

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    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
    • G01L5/00—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes
    • G01L5/12—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes for measuring axial thrust in a rotary shaft, e.g. of propulsion plants
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M15/00—Testing of engines
    • G01M15/14—Testing gas-turbine engines or jet-propulsion engines

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Force Measurement Appropriate To Specific Purposes (AREA)

Abstract

The application relates to the technical field of gas turbines, and discloses an axial force testing arrangement for test to gas turbine's rotor spare, gas turbine is equipped with the installation casket that is used for installing axial force testing arrangement, includes: one side of the air-floatation thrust bearing is connected to the mounting casing, and the other side of the air-floatation thrust bearing is used for being mounted on the end face of one side of the rotor piece along the axial direction; and the pressure sensor is arranged on the mounting casing and is used for acquiring an axial force signal of the air-floatation thrust bearing. The axial force testing device disclosed by the application can be used for obtaining an accurate axial force value and providing data support for the operation reliability of later-stage equipment of the gas turbine.

Description

Axial force testing device
Technical Field
The application relates to the technical field of gas turbines, in particular to an axial force testing device.
Background
For micro gas turbines that use air thrust bearings, the life of the axial load bearing directly determines the reliability of the equipment. Due to the structural characteristics of the bearing and the rotor, no means for directly acquiring true axial force exists in the production process of the gas turbine at present. The existing methods for acquiring the axial force are generally through simulation or through modeling, but the axial force acquired by the methods is inaccurate, so that the reliability of the operation of the later equipment is influenced.
Disclosure of Invention
The application can provide an axial force testing arrangement, can be used to obtain accurate axial force numerical value to for gas turbine later stage equipment operational reliability provide data support.
In order to achieve the above object, the present application provides an axial force testing device for testing a rotor member of a gas turbine provided with a mounting case for mounting the axial force testing device, the axial force testing device comprising:
one side of the air-floatation thrust bearing is connected to the mounting casing, and the other side of the air-floatation thrust bearing is used for being mounted on the end face of one side of the rotor piece along the axial direction;
and the pressure sensor is arranged on the mounting casing and is used for acquiring an axial force signal of the air-floatation thrust bearing.
The application provides an axial force testing arrangement sets up air supporting thrust bearing through along axial one side terminal surface at rotor spare to utilize pressure sensor to gather air supporting thrust bearing's axial force signal. When the gas turbine runs and the rotor part generates axial force, the axial force can be transmitted to the air-floatation thrust bearing by the rotor part and then transmitted to the pressure sensor by the air-floatation thrust bearing, and the pressure sensor can convert the axial force into force data so as to measure the axial force data of the rotor part.
The application provides an axial force testing arrangement, but the axial force data of direct acquisition rotor spare to the axial force data is accurate, can provide data support for gas turbine later stage equipment operational reliability.
Preferably, the axial force testing device further comprises a mounting disc, a groove is formed in one side, facing the rotor part, of the mounting casing, and the mounting disc is fixedly mounted in the groove;
one side of the air-floatation thrust bearing is connected to the mounting disc so as to be connected to the mounting casing through the mounting disc;
the pressure sensor is fixedly connected to the mounting plate.
Preferably, the axial force testing device further comprises a thrust bearing pressure plate, one side of the thrust bearing pressure plate is connected to the mounting disc, the other side of the thrust bearing pressure plate is connected to one side, away from the rotor member, of the air floatation thrust bearing, and two opposite sides of the thrust bearing pressure plate are respectively abutted to the air floatation thrust bearing and the pressure sensor.
Preferably, the thrust bearing pressure plate is fixedly mounted to the mounting plate by a positioning pin.
Preferably, the axial force testing device further comprises a temperature sensor, wherein the temperature sensor is fixed on the mounting disc and used for detecting the temperature of the air-bearing thrust bearing and the temperature of the pressure sensor.
Preferably, the axial force testing device further comprises a cooling assembly, and the cooling assembly is used for cooling the air floatation thrust bearing and the pressure sensor.
Preferably, the cooling assembly comprises a cooling channel arranged in the mounting disc, one end of the cooling channel is communicated with a cold source, and the other end of the cooling channel penetrates through the side wall of the mounting disc and is arranged close to the air thrust bearing and the pressure sensor.
Preferably, the mounting plate is detachably connected with the mounting casing.
Preferably, the mounting plate is mounted to the mounting case by fastening bolts.
Drawings
FIG. 1 is a schematic view of an axial force testing device mounted to a gas turbine according to an embodiment of the present disclosure;
FIG. 2 is a schematic view of an axial force testing device mounted on a gas turbine according to an embodiment of the present disclosure;
FIG. 3 is a schematic view of another embodiment of the axial force testing device of FIG. 2 mounted to a gas turbine engine;
FIG. 4 is a schematic view of another structure of the axial force testing device mounted on the gas turbine according to the embodiment of the present application.
In the figure:
10-a rotor piece; 20-axial force testing means; 21-mounting a disc; 22-an air-floating thrust bearing; 23-thrust bearing plate; 24-a pressure sensor; 25-a temperature sensor; 26-fastening bolts; 27-a locating pin; 30-installing a casing; 31-a groove; 40-a transmission shaft.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Referring to fig. 1, an axial force testing device 20 is provided according to an embodiment of the present disclosure, and the axial force testing device 20 may be used for testing an axial force of a rotor member 10 of a gas turbine. The gas turbine may be provided with a mounting case 30 for mounting the axial force testing device 20 to ensure that the axial force testing device 20 can be fixed to the gas turbine during the testing of the axial force, thereby facilitating obtaining accurate axial force data.
The axial force testing device 20 may include a mounting plate 21, an air bearing 22, a thrust bearing pressure plate 23, and a pressure sensor 24. The mounting casing 30 of the gas turbine may be disposed at a position close to the rotor member 10, a groove 31 may be disposed at a side of the mounting casing 30 facing the rotor member 10, the mounting plate 21 may be fixedly mounted in the groove 31, and two opposite sides of the mounting plate 21 may respectively abut against a sidewall of the groove 31, so that the mounting plate 21 and the groove 31 may be tightly connected.
The mounting plate 21 and the groove 31 may be detachably connected, for example, the mounting plate 21 may be connected to the bottom of the groove 31 by the fastening bolts 26, the number of the fastening bolts 26 may be two, one fastening bolt 26 may be disposed near one sidewall of the groove 31, the other fastening bolt 26 may be disposed near the other sidewall of the groove 31, and the two fastening bolts 26 may be in a symmetrical state, so that the force applied to the mounting plate 21 is balanced.
One side of the mounting disc 21, which is away from the bottom of the groove 31, can protrude out of the surface of the mounting case 30, so that the mounting disc 21 can be conveniently taken out of the mounting case 30 after the rotor member 10 is tested, and the operation is convenient.
The thrust bearing plate 23 may be provided at a side of the mounting plate 21 facing the rotor member 10, and the thrust bearing plate 23 may be mounted on the mounting plate 21 by a positioning pin 27 to play a role of bearing-fixing the thrust bearing plate.
The air thrust bearing 22 may be disposed on a side of the thrust bearing pressure plate 23 away from the mounting disk 21, and one side of the air thrust bearing 22 may abut against a surface of the thrust bearing pressure plate 23, and the other side may abut against an end surface of the rotor member 10 in the axial direction. Thus, when the rotor member 10 generates an axial force, the axial force is transmitted to the air thrust bearing 22.
The mounting disk 21 is provided with a cavity (not shown in fig. 1) opened toward the air thrust bearing 22, a pressure sensor 24 of the thrust bearing pressure plate 23 may be disposed in the cavity, and the pressure sensor 24 may be connected with a side surface of the thrust bearing pressure plate 23 facing away from the air thrust bearing 22. After the axial force of the rotor 10 is transmitted to the air-floating thrust bearing 22, the axial force is transmitted to the thrust bearing pressure plate 23 by the air-floating thrust bearing 22, then the thrust bearing pressure plate 23 transmits the axial force to the pressure sensor 24, and the pressure sensor 24 can convert the received axial force into force data, so that the axial force data of the rotor 10 can be obtained.
It will be appreciated that the mounting plate 21, the thrust bearing plate 23 and the air thrust bearing 22 may be annular, and the shape of each structure may correspond to the shape of the rotor member 10, such that the air thrust bearing 22 may be attached to the surface of the rotor member 10 around the rotor member 10, such that the axial force of the rotor member 10 may be uniformly transmitted to the air thrust bearing 22 and then to the thrust bearing plate 23.
In some embodiments, the axial force testing device 20 may further include a temperature sensor 25, the temperature sensor 25 may be disposed in the mounting plate 21, and the temperature sensor 25 may be fixedly attached to a side surface of the thrust bearing pressure plate 23 facing away from the air thrust bearing 22. Under different temperature environments, the temperature of the air thrust bearing 22 is different, and the measured axial force is also different. The air-floating thrust bearing 22 can transfer heat to the thrust bearing pressure plate 23 in the testing process, then transfer the temperature to the temperature sensor 25 through the thrust bearing pressure plate 23, and the temperature sensor 25 can obtain the temperature of the thrust bearing pressure plate 23 through data processing. When the axial force of the rotor element 10 is finally calculated, the accurate axial force magnitude can be calculated by combining the values of the temperature sensor 25 and the pressure sensor 24.
In some embodiments, the axial force testing device 20 may also include a cooling assembly (not shown in FIG. 1) that may be used to cool the air thrust bearing 22, the thrust bearing backing plate 23, and the pressure sensor 24. In one embodiment, the cooling assembly may include a cooling channel (not shown in fig. 1) disposed in the mounting plate 21, and one end of the cooling channel may be connected to a cooling source, which may be a cooling gas. The other end of the cooling channel may penetrate through the side wall of the mounting plate 21 and be disposed close to the air thrust bearing 22 and the pressure sensor 24, so that the cooling gas may cool the air thrust bearing 22 and the pressure sensor 24 through the cooling channel to satisfy the conditions of the axial force testing apparatus 20 at different testing temperatures.
In one implementation, the thrust bearing plate 23 may cover the opening of the cavity such that the cavity forms a relatively closed cavity under the action of the thrust bearing plate 23. The other end of the cooling channel may be disposed within the chamber such that the chamber may be filled with a cooling gas. In one aspect, because the pressure sensor 24 is located within the chamber, the pressure sensor 24 may be cooled. On the other hand, since the thrust bearing support plate 23 can directly contact with the cooling gas, the cooling gas can cool the thrust bearing support plate 23, and when there is a temperature difference between the thrust bearing support plate 23 and the air thrust bearing 22, the air thrust bearing 22 with a high temperature can transfer the temperature to the thrust bearing support plate 23 with a low temperature, thereby cooling the air thrust bearing 22.
In another implementation, the size of the air thrust bearing 22 in the radial direction of the rotor member 10 may be larger than the size of the thrust bearing pressure plate 23, that is, the orthographic projection of the air thrust bearing 22 on the surface of the mounting disk 21 facing the rotor member 10 can completely cover the orthographic projection of the thrust bearing pressure plate 23 on the surface of the mounting disk 21. At this time, an opening may be formed at a position of the mounting plate 21 facing the air thrust bearing 22, and the other end of the cooling passage may be communicated with the opening, so that the cooling gas may contact the surface of the air thrust bearing 22 through the opening, thereby achieving an effect of cooling the air thrust bearing 22. In addition, the chamber may also be in communication with the aperture such that cooling gas may enter the chamber and cool the pressure sensor 24.
With continued reference to FIG. 1, when the rotor member 10 of the gas turbine has axial force on only one side, the axial force testing device 20 may be mounted on the side where the axial force is generated.
Referring to fig. 2 and 3, when axial force is generated on both sides of the rotor member 10 of the gas turbine, the axial force testing device 20 may be installed on both sides of the rotor member 10 in the axial direction.
Referring to fig. 4, when two rotor members 10 are mounted on both ends of the same drive shaft 40, an axial force testing device 20 may be provided on a side of each rotor member 10 facing away from the other rotor member 10.
Compared with the existing axial force testing method, the axial force testing device is simple in overall structure design and high in feasibility. And the axial force value of the gas turbine under the actual application working condition can be directly obtained, the test cost and the test accuracy are greatly reduced, and data are provided for the design of the operational reliability of the micro gas turbine.
It will be apparent to those skilled in the art that various changes and modifications may be made in the embodiments of the present invention without departing from the spirit and scope of the invention. Thus, if such modifications and variations of the present invention fall within the scope of the claims of the present invention and their equivalents, the present invention is also intended to include such modifications and variations.

Claims (9)

1. An axial force testing device for testing a rotor member of a gas turbine provided with a mounting case for mounting the axial force testing device, comprising:
one side of the air-floatation thrust bearing is connected to the mounting casing, and the other side of the air-floatation thrust bearing is used for being mounted on the end face of one side of the rotor piece along the axial direction;
and the pressure sensor is arranged on the mounting casing and is used for acquiring an axial force signal of the air-floatation thrust bearing.
2. The axial force testing device of claim 1, further comprising a mounting plate, wherein a side of said mounting casing facing said rotor member is provided with a groove, and said mounting plate is fixedly mounted in said groove;
one side of the air-floatation thrust bearing is connected to the mounting disc so as to be connected to the mounting casing through the mounting disc;
the pressure sensor is fixedly connected to the mounting plate.
3. The axial force testing device of claim 2, further comprising a thrust bearing support plate, wherein one side of the thrust bearing support plate is connected to the mounting plate, the other side of the thrust bearing support plate is connected to a side of the air-thrust bearing facing away from the rotor member, and two opposite sides of the thrust bearing support plate are respectively abutted to the air-thrust bearing and the pressure sensor.
4. The axial force testing device of claim 3, wherein the thrust bearing backing plate is fixedly mounted to the mounting plate by a locating pin.
5. The axial force testing device of claim 2, further comprising a temperature sensor secured to the mounting plate and configured to sense a temperature of the air thrust bearing and the pressure sensor.
6. The axial force testing device of claim 5, further comprising a cooling assembly for cooling the air thrust bearing and the pressure sensor.
7. The axial force testing device of claim 6, wherein the cooling assembly comprises a cooling channel disposed in the mounting plate, one end of the cooling channel is communicated with a cold source, and the other end of the cooling channel penetrates through a side wall of the mounting plate and is disposed near the air thrust bearing and the pressure sensor.
8. The axial force testing device of claim 2, wherein said mounting plate is removably coupled to said mounting case.
9. The axial force testing device of claim 8, wherein said mounting plate is mounted to said mounting case by fastening bolts.
CN202210770169.XA 2022-06-30 2022-06-30 Axial force testing device Pending CN115060404A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202210770169.XA CN115060404A (en) 2022-06-30 2022-06-30 Axial force testing device

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202210770169.XA CN115060404A (en) 2022-06-30 2022-06-30 Axial force testing device

Publications (1)

Publication Number Publication Date
CN115060404A true CN115060404A (en) 2022-09-16

Family

ID=83204054

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202210770169.XA Pending CN115060404A (en) 2022-06-30 2022-06-30 Axial force testing device

Country Status (1)

Country Link
CN (1) CN115060404A (en)

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