CN113738458A - Gas turbine, device for preventing rotor from thermal bending and prime mover thereof - Google Patents
Gas turbine, device for preventing rotor from thermal bending and prime mover thereof Download PDFInfo
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- CN113738458A CN113738458A CN202010474785.1A CN202010474785A CN113738458A CN 113738458 A CN113738458 A CN 113738458A CN 202010474785 A CN202010474785 A CN 202010474785A CN 113738458 A CN113738458 A CN 113738458A
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- rotor
- electromagnet
- magnetic body
- motion output
- linear motion
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- 238000005452 bending Methods 0.000 title claims abstract description 25
- 230000002265 prevention Effects 0.000 claims abstract description 4
- CWYNVVGOOAEACU-UHFFFAOYSA-N Fe2+ Chemical compound [Fe+2] CWYNVVGOOAEACU-UHFFFAOYSA-N 0.000 claims 1
- 230000005540 biological transmission Effects 0.000 abstract description 4
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 16
- 238000007906 compression Methods 0.000 description 13
- 230000006835 compression Effects 0.000 description 11
- 229910052742 iron Inorganic materials 0.000 description 8
- RLQJEEJISHYWON-UHFFFAOYSA-N flonicamid Chemical compound FC(F)(F)C1=CC=NC=C1C(=O)NCC#N RLQJEEJISHYWON-UHFFFAOYSA-N 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 238000000418 atomic force spectrum Methods 0.000 description 2
- 238000007599 discharging Methods 0.000 description 2
- 238000013003 hot bending Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000012360 testing method Methods 0.000 description 2
- 230000003213 activating effect Effects 0.000 description 1
- 230000008602 contraction Effects 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
Images
Classifications
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- 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/34—Turning or inching gear
- F01D25/36—Turning or inching gear using electric motors
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- 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/12—Cooling
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/32—Arrangement, mounting, or driving, of auxiliaries
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01F—MAGNETS; INDUCTANCES; TRANSFORMERS; SELECTION OF MATERIALS FOR THEIR MAGNETIC PROPERTIES
- H01F7/00—Magnets
- H01F7/06—Electromagnets; Actuators including electromagnets
- H01F7/08—Electromagnets; Actuators including electromagnets with armatures
- H01F7/16—Rectilinearly-movable armatures
Abstract
The invention provides a gas turbine, a device for preventing rotor from thermal bending and a prime mover thereof, wherein an electromagnet and a magnetic body are oppositely arranged in the prime mover; the spring is connected with the electromagnet and the magnetic body; the linear motion output piece is connected with one of the electromagnet or the magnetic body in a follow-up manner; the storage battery is electrically connected with the electromagnet so that the electromagnet generates electromagnetic force and attracts the magnetic body; the spring is arranged to resist an attractive force between the electromagnet and the magnetic body; the device for preventing the rotor from being bent thermally comprises any one of the prime mover, a rotary motion output piece and an overrunning clutch; the gas turbine comprises a rotor, any one of the rotor thermal bending prevention devices and a control device. The invention adopts a small amount of components with simple structures to replace the motor and the transmission device thereof, effectively slows down or eliminates the problem of thermal bending of the rotor after the engine is stopped, and has lower cost.
Description
Technical Field
The invention relates to the technical field of aero-engines, in particular to a gas turbine, a device for preventing rotor from being thermally bent and a prime mover thereof.
Background
After the aircraft engine is stopped, the upper part of the engine is hot and the lower part of the engine is cold due to the non-uniformity of heat distribution in the engine, so that the engine rotor is bent and deformed due to expansion caused by heat and contraction caused by cold. The bent rotor may cause increased vibration of the engine and even mechanical damage when in operation. Before the engine is started, the engine can be forcibly cooled by performing cold operation for several times, so that the degree of thermal bending of the rotor is reduced, but the starting time of the engine is increased.
Other methods may also be used to slow the degree of thermal bowing of the rotor so that the engine can be started directly. FOR example, U.S. Pat. No. 4, 20180306065, 1 entitled "automatic ROTATION DEVICE FOR A GAS TURBINE ENGINE AND A METHOD OF COOLING A ROTATION OF A GAS TURBINE OF GAS TURBINE ENGINE utilizing AN automatic ROTATION DEVICE" discloses AN AUXILIARY rotating DEVICE FOR a GAS TURBINE ENGINE in the patent publication published as 2018, 10 and 25. This supplementary rotary device includes: an electric machine configured to be coupled to a rotor of a gas turbine engine; and a dedicated electrical storage device coupled to the motor. During operation of the gas turbine engine, the electric machine is configured to act as a generator to charge the dedicated electrical storage device. After the gas turbine engine is shut down, the electric machine is configured to act as a motor, powered by a dedicated electrical storage device, to rotate the rotor for a period of time to uniformly cool the rotor about its circumference.
The additional installation of the motor on the engine increases the cost.
Disclosure of Invention
The invention aims to provide a gas turbine, a device for preventing rotor thermal bending and a prime mover thereof, which adopt a small number of parts with simple structures to replace a motor and a transmission device thereof, effectively slow down or eliminate the problem of rotor thermal bending after an engine is stopped and have lower cost.
To achieve the above object, a prime mover for a device for preventing thermal bending of a rotor, comprising: a magnetic body; an electromagnet arranged opposite to the magnetic body; a spring connecting the electromagnet and the magnetic body; the linear motion output piece is connected with one of the electromagnet or the magnetic body in a follow-up manner; the storage battery is electrically connected with the electromagnet so that the electromagnet generates electromagnetic force and attracts the magnetic body; wherein the spring is arranged to resist an attractive force between the electromagnet and the magnetic body.
In one or more embodiments of the prime mover, the magnetic body is an iron mount and is fixed, and the electromagnet is fixed to one end of the linear motion output member.
In one or more embodiments of the prime mover, the linear motion output is a rack.
In one or more embodiments of the prime mover, the prime mover further comprises a switching device disposed between the electromagnet and the battery to control the electrical connection.
To achieve the object, an apparatus for preventing thermal bending of a rotor includes: any of the foregoing motive devices; the rotary motion output part is connected with the linear motion output part, is driven by the linear motion output part, and converts the linear motion of the linear motion output part into rotary motion; and an overrunning clutch for connecting the rotational motion output member and the rotational shaft of the rotor.
In one or more embodiments of the device for preventing thermal bending of a rotor, the linear motion output is a rack and the rotary motion output comprises gear sets having different gear ratios for different types of engines, any one of the gear sets being selectively disposed between the prime mover and the overrunning clutch.
To achieve the object, a gas turbine includes a rotor, and further includes: any one of the above-mentioned devices for preventing thermal bending of the rotor is connected with the rotating shaft of the rotor through an overrunning clutch; and a control device for triggering the motive power device of the rotor thermal bending prevention device after the gas turbine is stopped so as to drive the rotor to rotate.
In one or more embodiments of the gas turbine, the rotor is a high pressure rotor of the gas turbine.
The invention adopts a small amount of components with simple structures to replace the motor and the transmission device thereof, so that the rotor rotates slowly after the engine stops, the rotor component is ensured not to stay at the upper part or the lower part of the engine for a long time, the rotor is uniformly cooled around the circumference of the rotor, the problem of hot bending of the rotor after the engine stops is effectively slowed down or eliminated, the number of cold running times before the engine is started can be reduced or completely eliminated, the operation complexity is reduced, the starting time is shortened, the safety of the engine is improved, the cost is lower, and the invention is not only suitable for aeroengines, but also suitable for ground gas turbines and marine gas turbines.
Drawings
The above and other features, properties and advantages of the present invention will become more apparent from the following description of the embodiments with reference to the accompanying drawings, in which:
fig. 1 is a block diagram of an apparatus for preventing thermal bowing of a rotor according to one or more embodiments.
Fig. 2 is a schematic structural view of a device for preventing thermal bending of a rotor according to one or more embodiments.
Fig. 3 is a schematic view of an electrical connection between an electromagnet and a battery of a device for preventing thermal bending of a rotor according to one or more embodiments.
Fig. 4 is a schematic diagram of a spring force curve and an electromagnet magnetic force curve of a device for preventing thermal bending of a rotor according to one or more embodiments.
Fig. 5 is a schematic diagram of a rotor rotation angle versus spring compression for an apparatus for preventing thermal bending of a rotor according to one or more embodiments.
Detailed Description
The following discloses many different embodiments or examples for implementing the subject technology described. Specific examples of components and arrangements are described below to simplify the present disclosure, but these are merely examples and do not limit the scope of the invention. For example, if a first feature is formed over or on a second feature described later in the specification, this may include embodiments in which the first and second features are formed in direct contact, and may also include embodiments in which additional features are formed between the first and second features, such that the first and second features may not be in direct contact. Additionally, reference numerals and/or letters may be repeated among the various examples throughout this disclosure. This repetition is for the purpose of simplicity and clarity and does not in itself dictate a relationship between the various embodiments and/or configurations discussed. Further, when a first element is described as being coupled or coupled to a second element, the description includes embodiments in which the first and second elements are directly coupled or coupled to each other, as well as embodiments in which one or more additional intervening elements are added to indirectly couple or couple the first and second elements to each other.
Referring to fig. 1 and 2, the device for preventing thermal bending of a rotor includes a prime mover 1, a rotational motion output member 2, and an overrunning clutch 3.
The prime mover 1 includes a magnetic body 11, a spring 12, an electromagnet 13, a linear motion output member 14, and a battery 15. The magnetic body 11 and the electromagnet 13 are arranged oppositely and connected through a spring 12, the spring 12 is arranged to resist the attraction force between the magnetic body 11 and the electromagnet 13, the linear motion output piece 14 is connected with one of the magnetic body 11 or the electromagnet 13 in a follow-up mode, and the storage battery 15 is electrically connected with the electromagnet 13, so that the electromagnet 13 generates electromagnetic force to attract the magnetic body 11.
The rotary motion output part 2 is connected with the linear motion output part 14, is driven by the linear motion output part 14, and is used for converting the linear motion of the linear motion output part 14 into rotary motion so as to drive the rotating shaft 4 of the engine rotor to rotate.
The overrunning clutch 3 is used for connecting the rotary motion output part 2 and a rotating shaft 4 of the engine rotor, and the overrunning clutch 3 is set to be meshed with the rotating shaft 4 through the overrunning clutch 3 when the rotating speed of the rotary motion output part 2 is greater than that of the rotating shaft 4, so as to drive the rotating shaft 4 to rotate, so that the rotor continues to rotate for a period of time after the engine is stopped, and the rotor is uniformly cooled around the circumference of the rotor; when the rotational speed of the rotary output element 2 is less than the rotational speed of the rotary shaft 4, the rotary output element 2 is disengaged from the rotary shaft 4 and the engine operates independently.
In some embodiments, as shown in fig. 3, the prime mover 1 further comprises a switching device 16 arranged between the electromagnet 13 and the accumulator 15 to control the electrical connection therebetween, as well as the charging and discharging of the accumulator 15. When the switching device 16 switches on the power supply 17, the storage battery 15 is charged, and the electromagnet 13 is in an off state; when the switching device 16 turns on the electromagnet 13, the battery 15 is discharged and the electromagnet 13 starts to operate. Examples of switching devices 16 include, but are not limited to, single pole double throw switches or single pole triple throw switches. When a single pole double throw switch is employed, the charging and discharging modes of the battery 15 are mutually exclusive; when the single-pole-three-throw switch is used, the secondary battery 15 can be in an off state in addition to the charge and discharge mode.
In some embodiments, the magnetic body 11 is an iron mount and is fixedly disposed, the electromagnet 13 is disposed at one end of the linear motion output member 14, and when the circuit between the battery 15 and the electromagnet 13 is completed, an electromagnetic force is generated between the electromagnet 13 and the iron mount, and the electromagnetic force pulls the electromagnet 13 and the linear motion output member 14 to move toward the iron mount and compresses the spring 12. As the distance between the electromagnet 13 and the iron material mount is shortened, the electromagnetic force increases, the elastic force of the spring 12 due to compression also increases, and finally, a state in which the electromagnetic force and the elastic force are balanced is achieved.
Referring to fig. 4, the abscissa X represents the compression amount of the spring 12, and the ordinate represents the electromagnetic force F between the electromagnet 13 and the iron member mounting seatmOr spring force F of spring 12k Curves 100, 200, 300 represent the electromagnetic force F at 100%, 50% and 20% of the charge of the accumulator 15, respectivelym Curve 400 spring force F for curve X of the amount of compressionk-compression X-curve. When the electric quantity of the storage battery 15 is 100%, the compression quantity of the elastic force and the electromagnetic force is X100Force balance is achieved; when the charge of the battery 15 decreases, the electromagnetic force FmThe curve of the compression X is varied, but the spring force FkConstant curve of the compression X, electromagnetic force FmWith elastic force FkThe equilibrium point of (a) corresponds to the amount of compression of the spring 12 that varies with time.
The invention adopts a storage battery 15 with short discharge time, and the discharge time selection range is 10min to 3 h. When the circuit between the storage battery 15 and the electromagnet 13 is switched on, the electromagnet 13 starts to work to drive the linear motion output piece 14 to move towards the iron material mounting seat, and the spring 12 is compressed to the initial compression amount, namely the maximum compression amount X100. Along with the reduction of the electric quantity of the storage battery 15, the electromagnetic force is reduced, the compression amount of the spring 12 is reduced, the electromagnet 13 drives the linear motion output part 14 to move towards the direction far away from the iron material mounting seat, and the rotary motion output part 2 drives the rotary shaft 4 of the rotor and the blades and the discs connected with the rotary shaft to rotate, so that the rotor part is ensured not to stay at the upper part or the lower part of the engine for a long time, the rotor is uniformly cooled around the circumference of the engine, and the thermal bending of the rotor caused by nonuniform heating is reduced or eliminated.
In some embodiments, the linear motion output 14 is a rack and the rotary motion output 2 comprises gear sets with different gear ratios for different types of engines, and the device for preventing rotor thermal bowing can be used to test a number of different types of engines. Since the angle of rotation theta of the rotatable shaft 4 is inversely proportional to the amount of compression X of the spring 12, as shown in figure 5, and the slope of the theta-X curve is determined by the ratio of the gearsets, one of the gearsets was selected to fit between the prime mover 1 and the overrunning clutch 3 for different types of engines during testing and at least ensured that the maximum value of theta exceeded 360 deg..
In some embodiments, the linear motion output 14 can also be configured as a worm or a threaded rod, and the rotary motion output 2 can be configured as a worm gear or a nut.
In some embodiments, the gas turbine using the device for preventing thermal bending of a rotor according to the present invention further comprises a control device (not shown) for activating the prime mover 1 to drive the rotor to rotate after the gas turbine is stopped.
In some embodiments, the rotor thermal bowing prevention device of the present invention is used in a high pressure rotor of a gas turbine. The high pressure rotor has a higher working temperature and is more prone to thermal bowing.
The invention adopts a small amount of components with simple structures to replace the motor and the transmission device thereof, so that the rotor rotates slowly after the engine stops, the rotor component is ensured not to stay at the upper part or the lower part of the engine for a long time, the rotor is uniformly cooled around the circumference of the rotor, the problem of hot bending of the rotor after the engine stops is effectively slowed down or eliminated, the number of cold running times before the engine is started can be reduced or completely eliminated, the operation complexity is reduced, the starting time is shortened, the safety of the engine is improved, the cost is lower, and the invention is not only suitable for aeroengines, but also suitable for ground gas turbines and marine gas turbines.
Although the present invention has been disclosed in terms of the preferred embodiment, it is not intended to limit the invention, and variations and modifications may be made by one skilled in the art without departing from the spirit and scope of the invention. Therefore, any modification, equivalent change and modification of the above embodiments according to the technical essence of the present invention are within the protection scope defined by the claims of the present invention, unless the technical essence of the present invention departs from the content of the present invention.
Claims (8)
1. A prime mover for a device for preventing thermal bowing of a rotor, comprising:
a magnetic body;
an electromagnet arranged opposite to the magnetic body;
a spring connecting the electromagnet and the magnetic body;
the linear motion output piece is connected with one of the electromagnet or the magnetic body in a follow-up manner; and
the storage battery is electrically connected with the electromagnet so that the electromagnet generates electromagnetic force and attracts the magnetic body;
wherein the spring is arranged to resist an attractive force between the electromagnet and the magnetic body.
2. The motive power device for preventing the thermal bending of the rotor according to claim 1, wherein said magnetic body is a ferrous mount and is fixedly provided, and said electromagnet is fixed to one end of said linear motion output member.
3. The motive means for preventing thermal bowing of a rotor of claim 1 wherein said linear motion output member is a rack.
4. The motive means for preventing thermal bending of a rotor as recited in claim 1, further comprising a switching means disposed between said electromagnet and said accumulator for controlling said electrical connection.
5. Device for preventing thermal bending of a rotor, comprising:
the motive device of any one of claims 1 to 4;
the rotary motion output part is connected with the linear motion output part, is driven by the linear motion output part, and converts the linear motion of the linear motion output part into rotary motion; and
and the overrunning clutch is used for connecting the rotary motion output piece and the rotating shaft of the rotor.
6. The device of claim 5 wherein the linear motion output is a rack and the rotary motion output includes gear sets having different gear ratios for different types of engines, any one of the gear sets being selectively disposed between the prime mover and the overrunning clutch.
7. A gas turbine engine comprising a rotor, characterized by:
the device for preventing rotor thermal bending according to claim 5 or 6, wherein the rotating shaft of the rotor is connected with an overrunning clutch; and
and the control device triggers the motive power device of the rotor thermal bending prevention device after the gas turbine is stopped so as to drive the rotor to rotate.
8. The gas turbine of claim 7, wherein said rotor is a high pressure rotor of said gas turbine.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010474785.1A CN113738458B (en) | 2020-05-29 | 2020-05-29 | Gas turbine, rotor heat bending prevention device and driving device thereof |
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| CN202010474785.1A CN113738458B (en) | 2020-05-29 | 2020-05-29 | Gas turbine, rotor heat bending prevention device and driving device thereof |
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| CN113738458A true CN113738458A (en) | 2021-12-03 |
| CN113738458B CN113738458B (en) | 2023-09-29 |
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| 杜生广，赵明等: "《防止和减少航空发动机热弯曲故障方法的研究》", 《燃气涡轮试验与研究》, pages 43 - 47 * |
| 王凤森，王泽钦等: "《温度梯度对航空发动机转子热弯曲的影响分析》", 《汽轮机技术》, vol. 60, no. 6, pages 443 - 446 * |
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| CN113738458B (en) | 2023-09-29 |
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