WO2017028316A1 - Gas turbine and starting device thereof - Google Patents
Gas turbine and starting device thereof Download PDFInfo
- Publication number
- WO2017028316A1 WO2017028316A1 PCT/CN2015/087692 CN2015087692W WO2017028316A1 WO 2017028316 A1 WO2017028316 A1 WO 2017028316A1 CN 2015087692 W CN2015087692 W CN 2015087692W WO 2017028316 A1 WO2017028316 A1 WO 2017028316A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- gas turbine
- rotating shaft
- stator
- rotor
- main shaft
- Prior art date
Links
Classifications
-
- 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
- F02C7/26—Starting; Ignition
- F02C7/268—Starting drives for the rotor, acting directly on the rotor of the gas turbine to be started
Definitions
- the invention relates to a starting device for a gas turbine, in particular to a starting device capable of reducing energy consumption and a gas turbine thereof.
- the rotating shaft of the starting motor is combined with the main shaft of the gas turbine to drive the gas turbine main shaft to its own self-sustaining speed.
- the starting motor shaft is separated from the gas turbine main shaft.
- the output shaft of the starting motor and the gas turbine main shaft are driven by the tooth connection, but the starting motor shaft and the gas turbine main shaft are often so that the teeth are disengaged and the joint teeth are easily worn.
- this paper proposes a starting device that is simple in structure and can effectively solve the wear problem.
- a gas turbine starting device for propelling a gas turbine includes a stator and a rotor rotating relative to the stator, the rotor including a rotating shaft and a permanent magnet fixed to the rotating shaft, a rotating shaft of the rotor and the gas turbine
- the spindle fixed connection enables the rotating shaft to rotate coaxially with the spindle
- the stator surrounds the rotating shaft and is arranged to be axially movable relative to the rotating shaft
- the stator is located during the starting of the gas turbine
- the rotating shaft is in a position facing in the radial direction. When the rotational speed of the main shaft of the gas turbine exceeds a predetermined rotational speed, the stator axially moves outside the radial range of the rotating shaft.
- the rotating shaft of the rotor is a separate component fixedly coupled to the main shaft of the gas turbine, and the rotating shaft is coupled to the direct drive of the spindle.
- the rotating shaft of the rotor is integrally formed with the main shaft as part of the main shaft of the gas turbine.
- the predetermined rotational speed is a self-sustaining rotational speed of the gas turbine.
- a gas turbine including a gas turbine main shaft, a compressor and a turbine fixedly coupled to the gas turbine main shaft, and a combustion chamber coupled between the compressor and the turbine, the gas turbine further including a starting device
- the starting device includes a stator and a rotor that rotates relative to the stator, the rotor includes a rotating shaft and a permanent magnet fixed to the rotating shaft, and a rotating shaft of the rotor is fixedly coupled with a main shaft of the gas turbine such that the rotating shaft can be
- the main shaft rotates coaxially
- the stator surrounds the rotating shaft and is arranged to be axially movable relative to the rotating shaft, and during the starting of the gas turbine, the stator is located in a position orthogonal to the rotating shaft in a radial direction. After the spindle speed of the gas turbine exceeds a predetermined speed, the stator moves axially beyond the radial extent of the shaft.
- the rotating shaft of the rotor is a separate component fixedly coupled to the main shaft of the gas turbine, and the rotating shaft is coupled to the direct drive of the spindle.
- the rotating shaft of the rotor is integrally formed with the main shaft as part of the main shaft of the gas turbine.
- the rotating shaft of the rotor extends integrally from the main shaft of the gas turbine to protrude from an end surface of the compressor.
- the predetermined rotational speed is a self-sustaining rotational speed of the gas turbine.
- the present invention provides a gas turbine starting device.
- the stator of the starting device is arranged to be axially movable relative to the rotating shaft.
- the stator is located in a radial direction opposite to the rotating shaft.
- the rotational speed of the gas turbine main shaft exceeds a predetermined rotational speed
- the rotating shaft is still driven by the main shaft of the gas turbine.
- the rotation is driven, and the stator is axially moved outside the radial range of the rotating shaft, so that the magnetic resistance of the stator electromagnetic coil to the rotation of the gas turbine main shaft can be overcome.
- the rotating shaft of the starting device is combined with the direct drive of the gas turbine main shaft to eliminate wear problems.
- Figure 1 is a simplified schematic diagram of the gas turbine starting device at startup.
- Figure 2 is a simplified schematic diagram of the gas turbine main shaft exceeding its self-sustaining speed.
- Figure 1 is a simplified schematic diagram of the gas turbine starting device at startup.
- the gas turbine includes a starting device 10, a combustion chamber 11, a gas turbine main shaft 12, and a compressor 14 and a turbine 16 fixedly coupled to the gas turbine main shaft 12.
- the starting device 10 is connected to the gas turbine main shaft 12 to drive the gas turbine, and the combustion chamber 11 is connected between the compressor 14 and the turbine 16.
- the starting device 10 includes a stator 18 and a rotor 20 that rotates relative to the stator 18.
- the rotor 20 includes a rotating shaft 22 and a permanent magnet 24 fixed to the rotating shaft 22, and the rotating shaft 22 is directly coupled to the gas turbine main shaft 12 such that the rotating shaft 22 can rotate coaxially with the gas turbine main shaft 12.
- the rotating shaft 22 of the rotor 20 is integrally formed with the gas turbine main shaft 12 as part of the gas turbine main shaft 12.
- the rotating shaft 22 of the rotor 20 extends integrally from the gas turbine main shaft 12 to protrude from the end surface of the compressor 14.
- the rotating shaft 22 of the rotor 20 can be a separate component that is fixedly coupled to the gas turbine main shaft 12, and the rotating shaft 22 is coupled to the direct drive of the gas turbine main shaft 12.
- the stator 18 is mounted about the axis of rotation 22 of the rotor 20 and is configured to be axially moveable relative to the rotating shaft 22, in particular, the stator 18 is located radially with the rotating shaft 22 during startup of the gas turbine. a position that is opposite; when the rotational speed of the main shaft 12 of the gas turbine exceeds a predetermined rotational speed, the stator 18 moves axially beyond the radial extent of the rotating shaft 22, such that when the gas turbine drives the rotating shaft 22 to rotate, due to the rotor 20 and the stator
- the 18 is spaced apart, and electromagnetic induction is not generated between the permanent magnet 24 of the rotor 20 and the coil of the stator 18, so that no magnetic resistance is generated.
- the above-mentioned predetermined rotational speed is the self-sustaining rotational speed of the gas turbine in this embodiment, that is, the gas turbine can be operated by itself without using the starting device 10.
- the working process of the present invention is such that, first, the starting device 10 operates to start the gas turbine. Specifically, the rotating shaft 22 of the starting device 10 rotationally drives the spindle 12 of the gas turbine to rotate, and the stator 18 is located radially opposite the rotating shaft 22 at this time. The position, in particular, the coil of the stator 18 is radially opposite the permanent magnet 24 of the rotor 20. Then, the compressor 14 starts to compress the air and deliver the compressed high-pressure air to the combustion chamber 11. The combustion chamber 11 is put into the fuel and ignited, and the high-temperature and high-pressure gas generated in the combustion chamber 11 enters the turbine 16 and drives the turbine 16 to operate. While the flat 16 is running, the gas turbine main shaft 12 is driven to rotate at a faster speed.
- the starting device 10 When the rotational speed of the gas turbine main shaft 12 reaches the self-sustaining rotational speed of the gas turbine, the starting device 10 does not need to continue to drive the gas turbine main shaft, and the gas turbine can operate autonomously. At this time, the stator 18 is axially moved outside the radial range of the rotating shaft 22 to be displaced from the permanent magnet 24 of the rotor 20, eliminating the reluctance of the starting motor.
- the present invention provides a gas turbine starting device.
- the stator of the starting device is arranged to be axially movable relative to the rotating shaft.
- the stator is located in a radial direction opposite to the rotating shaft.
- the rotational speed of the gas turbine main shaft exceeds a predetermined rotational speed
- the rotating shaft is still driven by the main shaft of the gas turbine.
- the rotation is driven, and the stator axially moves outside the radial range of the rotating shaft, so that the magnetic resistance of the stator electromagnetic coil to the rotor can be overcome, and the starting device has a simple structure and convenient installation, and can improve the effective power of the gas turbine and save cost.
- the rotating shaft of the starting device is combined with the direct drive of the gas turbine main shaft to eliminate wear problems.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Control Of Turbines (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)
Abstract
A starting device (10) for a gas turbine is used for starting the gas turbine and comprises a stator (18) and a rotor (20) rotating relative to the stator (18). The rotor (20) comprises a rotating shaft (22) and a permanent magnet (24) fixed to the rotating shaft (22). The rotating shaft (22) of the rotor (20) is fixedly connected to a main shaft (12) of the gas turbine so that the rotating shaft (22) and the main shaft (12) can coaxially rotate. The stator (18) surrounds the rotating shaft (22) and can move relative to the axial direction of the rotating shaft (22). In the process of starting the gas turbine, the stator (18) is located at the position exactly facing to the rotating shaft (22) in the radial direction. After the rotating speed of the main shaft (12) of the gas turbine exceeds a preset rotating speed, the stator (18) moves axially to the position out of the radial direction range of the rotating shaft (22).
Description
本发明涉及一种燃气轮机的启动装置，特别是涉及一种可减小能耗的启动装置及其燃气轮机。The invention relates to a starting device for a gas turbine, in particular to a starting device capable of reducing energy consumption and a gas turbine thereof.
现有的燃气轮机启动时，启动电机的转轴与燃气轮机的主轴结合，驱动燃气轮机主轴至其自持转速，燃烧室点火后，启动电机转轴与燃气轮机主轴脱离。然而，现有技术中启动电机的输出轴与燃气轮机主轴是以齿连接进行传动，但启动电机转轴与燃气轮机主轴经常这样齿合、脱离容易造成结合齿磨损。When the existing gas turbine is started, the rotating shaft of the starting motor is combined with the main shaft of the gas turbine to drive the gas turbine main shaft to its own self-sustaining speed. After the combustion chamber is ignited, the starting motor shaft is separated from the gas turbine main shaft. However, in the prior art, the output shaft of the starting motor and the gas turbine main shaft are driven by the tooth connection, but the starting motor shaft and the gas turbine main shaft are often so that the teeth are disengaged and the joint teeth are easily worn.
有鉴于此，本文提出一种结构简单且可有效解决磨损问题的启动装置。In view of this, this paper proposes a starting device that is simple in structure and can effectively solve the wear problem.
本文还提出一种利用上述启动装置的燃气轮机。A gas turbine utilizing the above described starting device is also presented herein.
本文提出的一种燃气轮机启动装置，用于启动燃气轮机，包括定子和相对于所述定子转动的转子，所述转子包括转轴以及固定至所述转轴的永磁体，所述转子的转轴与所述燃气轮机的主轴固定连接使得所述转轴能够与所述主轴同轴旋转，所述定子环绕所述转轴并设置成能够相对于所述转轴轴向移动，在所述燃气轮机启动过程中，所述定子位于与所述转轴在径向上正对的位置，当所述燃气轮机的主轴转速超过一预定转速后，所述定子轴向移动至所述转轴的径向范围之外。A gas turbine starting device for propelling a gas turbine includes a stator and a rotor rotating relative to the stator, the rotor including a rotating shaft and a permanent magnet fixed to the rotating shaft, a rotating shaft of the rotor and the gas turbine The spindle fixed connection enables the rotating shaft to rotate coaxially with the spindle, the stator surrounds the rotating shaft and is arranged to be axially movable relative to the rotating shaft, and the stator is located during the starting of the gas turbine The rotating shaft is in a position facing in the radial direction. When the rotational speed of the main shaft of the gas turbine exceeds a predetermined rotational speed, the stator axially moves outside the radial range of the rotating shaft.
在一实施例中，所述转子的转轴为固定连接至所述燃气轮机主轴的单独元件，所述转轴与所述主轴直驱结合。In an embodiment, the rotating shaft of the rotor is a separate component fixedly coupled to the main shaft of the gas turbine, and the rotating shaft is coupled to the direct drive of the spindle.
在一实施例中，所述转子的转轴作为所述燃气轮机主轴的一部分与所述主轴一体成型。In an embodiment, the rotating shaft of the rotor is integrally formed with the main shaft as part of the main shaft of the gas turbine.
在一实施例中，所述预定转速为所述燃气轮机的自持转速。In an embodiment, the predetermined rotational speed is a self-sustaining rotational speed of the gas turbine.
本文还提出一种燃气轮机，包括燃气轮机主轴，与所述燃气轮机主轴固定连接的压气机和透平以及连接在所述压气机和透平之间的燃烧室，所述燃气轮机还包括启动装置，所述启动装置包括定子和相对于所述定子转动的转子，所述转子包括转轴以及固定至所述转轴的永磁体，所述转子的转轴与所述燃气轮机的主轴固定连接使得所述转轴能够与所述主轴同轴旋转，所述定子环绕所述转轴并设置成能够相对于所述转轴轴向移动，在所述燃气轮机启动过程中，所述定子位于与所述转轴在径向上正对的位置，当所述燃气轮机的主轴转速超过一预定转速后，所述定子轴向移动至所述转轴的径向范围之外。Also presented herein is a gas turbine including a gas turbine main shaft, a compressor and a turbine fixedly coupled to the gas turbine main shaft, and a combustion chamber coupled between the compressor and the turbine, the gas turbine further including a starting device, The starting device includes a stator and a rotor that rotates relative to the stator, the rotor includes a rotating shaft and a permanent magnet fixed to the rotating shaft, and a rotating shaft of the rotor is fixedly coupled with a main shaft of the gas turbine such that the rotating shaft can be The main shaft rotates coaxially, the stator surrounds the rotating shaft and is arranged to be axially movable relative to the rotating shaft, and during the starting of the gas turbine, the stator is located in a position orthogonal to the rotating shaft in a radial direction. After the spindle speed of the gas turbine exceeds a predetermined speed, the stator moves axially beyond the radial extent of the shaft.
在一实施例中，所述转子的转轴为固定连接至所述燃气轮机主轴的单独元件，所述转轴与所述主轴直驱结合。In an embodiment, the rotating shaft of the rotor is a separate component fixedly coupled to the main shaft of the gas turbine, and the rotating shaft is coupled to the direct drive of the spindle.
在一实施例中，所述转子的转轴作为所述燃气轮机主轴的一部分与所述主轴一体成型。In an embodiment, the rotating shaft of the rotor is integrally formed with the main shaft as part of the main shaft of the gas turbine.
在一实施例中，所述转子的转轴自所述燃气轮机主轴一体地延伸而突出于所述压气机的端面。In an embodiment, the rotating shaft of the rotor extends integrally from the main shaft of the gas turbine to protrude from an end surface of the compressor.
在一实施例中，所述预定转速为所述燃气轮机的自持转速。In an embodiment, the predetermined rotational speed is a self-sustaining rotational speed of the gas turbine.
综上所述，本发明提供了一种燃气轮机启动装置。所述启动装置的定子设置成能够相对于转轴轴向移动，在燃气轮机启动过程中，定子位于与转轴在径向上正对的位置，当燃气轮机主轴的转速超过一预定转速后，转轴仍然被燃气轮机主轴带动旋转，此时定子轴向移动至转轴的径向范围之外，如此便可克服定子电磁线圈对燃气轮机主轴转动的磁阻。启动装置的转轴与燃气轮机主轴直驱结合，消除了磨损问题。In summary, the present invention provides a gas turbine starting device. The stator of the starting device is arranged to be axially movable relative to the rotating shaft. During the starting of the gas turbine, the stator is located in a radial direction opposite to the rotating shaft. When the rotational speed of the gas turbine main shaft exceeds a predetermined rotational speed, the rotating shaft is still driven by the main shaft of the gas turbine. The rotation is driven, and the stator is axially moved outside the radial range of the rotating shaft, so that the magnetic resistance of the stator electromagnetic coil to the rotation of the gas turbine main shaft can be overcome. The rotating shaft of the starting device is combined with the direct drive of the gas turbine main shaft to eliminate wear problems.
图1是燃气轮机启动装置启动时的简化示意图。Figure 1 is a simplified schematic diagram of the gas turbine starting device at startup.
图2是燃气轮机主轴超过自持转速后的简化示意图。Figure 2 is a simplified schematic diagram of the gas turbine main shaft exceeding its self-sustaining speed.
在详细描述实施例之前，应该理解的是，本发明不限于本申请中下文或附图中所描述的详细结构或元件排布。本发明可为其它方式实现的实施例。而且，应当理解，本文所使用的措辞及术语仅仅用作描述用途，不应作限定性解释。本文所使用的“包括”、“包含”、“具有”等类似措辞意为包含其后所列出之事项、其等同物及其它附加事项。特别是，当描述“一个某元件”时，本发明并不限定该元件的数量为一个，也可以包括多个。Before the embodiments are described in detail, it is understood that the invention is not limited to the details The invention may be embodied in other ways. Also, it will be understood that the phraseology and terminology used herein are for the purpose of description The words "including", "comprising", "having", and <RTIgt; </ RTI> <RTIgt; </ RTI> used herein are meant to include the items listed thereafter, their equivalents, and other additional items. In particular, when describing "a certain element", the invention does not limit the number of the elements to one, and may include a plurality.
图1是燃气轮机启动装置启动时的简化示意图。如图1所示，所述燃气轮机包括启动装置10，燃烧室11，燃气轮机主轴12以及与燃气轮机主轴12固定连接的压气机14和透平16。其中，启动装置10与燃气轮机主轴12连接以驱动所述燃气轮机运转，燃烧室11连接在压气机14和透平16之间。Figure 1 is a simplified schematic diagram of the gas turbine starting device at startup. As shown in FIG. 1, the gas turbine includes a starting device 10, a combustion chamber 11, a gas turbine main shaft 12, and a compressor 14 and a turbine 16 fixedly coupled to the gas turbine main shaft 12. Therein, the starting device 10 is connected to the gas turbine main shaft 12 to drive the gas turbine, and the combustion chamber 11 is connected between the compressor 14 and the turbine 16.
启动装置10包括定子18和相对于定子18转动的转子20。转子20包括转轴22以及固定至转轴22上的永磁体24，转轴22与燃气轮机主轴12直驱连接使得转轴22能够与燃气轮机主轴12同轴旋转。The starting device 10 includes a stator 18 and a rotor 20 that rotates relative to the stator 18. The rotor 20 includes a rotating shaft 22 and a permanent magnet 24 fixed to the rotating shaft 22, and the rotating shaft 22 is directly coupled to the gas turbine main shaft 12 such that the rotating shaft 22 can rotate coaxially with the gas turbine main shaft 12.
在本实施例中，转子20的转轴22作为燃气轮机主轴12的一部分与燃气轮机主轴12一体成型。例如，在一实施例中，转子20的转轴22自所述燃气轮机主轴12一体地延伸而突出于压气机14的端面。In the present embodiment, the rotating shaft 22 of the rotor 20 is integrally formed with the gas turbine main shaft 12 as part of the gas turbine main shaft 12. For example, in an embodiment, the rotating shaft 22 of the rotor 20 extends integrally from the gas turbine main shaft 12 to protrude from the end surface of the compressor 14.
在其他实施例中，转子20的转轴22可为固定连接至燃气轮机主轴12的单独元件，采取转轴22与燃气轮机主轴12直驱结合的方式连接。In other embodiments, the rotating shaft 22 of the rotor 20 can be a separate component that is fixedly coupled to the gas turbine main shaft 12, and the rotating shaft 22 is coupled to the direct drive of the gas turbine main shaft 12.
在所示的实施例中，定子18环绕转子20的转轴22安装并设置成能够相对于转轴22轴向移动，具体而言，在所述燃气轮机启动过程中，定子18位于与转轴22在径向上正对的位置；当所述燃气轮机的主轴12转速超过一预定转速后，定子18轴向移动至转轴22的径向范围之外，如此，所述燃气轮机带动转轴22转动时，由于转子20和定子18被隔开，转子20的永磁体24与定子18的线圈之间不会产生电磁感应，因此不会产生磁阻。In the illustrated embodiment, the stator 18 is mounted about the axis of rotation 22 of the rotor 20 and is configured to be axially moveable relative to the rotating shaft 22, in particular, the stator 18 is located radially with the rotating shaft 22 during startup of the gas turbine. a position that is opposite; when the rotational speed of the main shaft 12 of the gas turbine exceeds a predetermined rotational speed, the stator 18 moves axially beyond the radial extent of the rotating shaft 22, such that when the gas turbine drives the rotating shaft 22 to rotate, due to the rotor 20 and the stator The 18 is spaced apart, and electromagnetic induction is not generated between the permanent magnet 24 of the rotor 20 and the coil of the stator 18, so that no magnetic resistance is generated.
应当注意的是，上述预定转速在本实施例中为所述燃气轮机的自持转速，即不用启动装置10驱动所述燃气轮机也能自行运转。It should be noted that the above-mentioned predetermined rotational speed is the self-sustaining rotational speed of the gas turbine in this embodiment, that is, the gas turbine can be operated by itself without using the starting device 10.
本发明的工作过程是这样的，首先，启动装置10运转以启动燃气轮机，具体来说，启动装置10的转轴22转动驱动燃气轮机的主轴12转动，此时定子18位于与转轴22在径向上正对的位置，具体而言，定子18的线圈与转子20的永磁体24在径向上正对。然后，压气机14开始压缩空气并将压缩后的高压空气输送至燃烧室11，燃烧室11投入燃料并点火，燃烧室11内产生的高温高压气体进入透平16并带动透平16运转，透平16运转的同时带动燃气轮机主轴12以更快的速度转动，当燃气轮机主轴12的转速达到所述燃气轮机的自持转速后，启动装置10不需要继续驱动燃气轮机主轴，燃气轮机就可以自主运行。此时，定子18轴向移动至转轴22的径向范围之外以与转子20的永磁体24错开，消除启动电机的磁阻。The working process of the present invention is such that, first, the starting device 10 operates to start the gas turbine. Specifically, the rotating shaft 22 of the starting device 10 rotationally drives the spindle 12 of the gas turbine to rotate, and the stator 18 is located radially opposite the rotating shaft 22 at this time. The position, in particular, the coil of the stator 18 is radially opposite the permanent magnet 24 of the rotor 20. Then, the compressor 14 starts to compress the air and deliver the compressed high-pressure air to the combustion chamber 11. The combustion chamber 11 is put into the fuel and ignited, and the high-temperature and high-pressure gas generated in the combustion chamber 11 enters the turbine 16 and drives the turbine 16 to operate. While the flat 16 is running, the gas turbine main shaft 12 is driven to rotate at a faster speed. When the rotational speed of the gas turbine main shaft 12 reaches the self-sustaining rotational speed of the gas turbine, the starting device 10 does not need to continue to drive the gas turbine main shaft, and the gas turbine can operate autonomously. At this time, the stator 18 is axially moved outside the radial range of the rotating shaft 22 to be displaced from the permanent magnet 24 of the rotor 20, eliminating the reluctance of the starting motor.
综上所述，本发明提供了一种燃气轮机启动装置。所述启动装置的定子设置成能够相对于转轴轴向移动，在燃气轮机启动过程中，定子位于与转轴在径向上正对的位置，当燃气轮机主轴的转速超过一预定转速后，转轴仍然被燃气轮机主轴带动旋转，此时定子轴向移动至转轴的径向范围之外，如此便可克服定子电磁线圈对转子的磁阻，且此启动装置结构简单，安装方便，可提高燃气轮机有效功率，节约成本。启动装置的转轴与燃气轮机主轴直驱结合，消除了磨损问题。In summary, the present invention provides a gas turbine starting device. The stator of the starting device is arranged to be axially movable relative to the rotating shaft. During the starting of the gas turbine, the stator is located in a radial direction opposite to the rotating shaft. When the rotational speed of the gas turbine main shaft exceeds a predetermined rotational speed, the rotating shaft is still driven by the main shaft of the gas turbine. The rotation is driven, and the stator axially moves outside the radial range of the rotating shaft, so that the magnetic resistance of the stator electromagnetic coil to the rotor can be overcome, and the starting device has a simple structure and convenient installation, and can improve the effective power of the gas turbine and save cost. The rotating shaft of the starting device is combined with the direct drive of the gas turbine main shaft to eliminate wear problems.
本文所描述的概念在不偏离其精神和特性的情况下可以实施成其它形式。所公开的具体实施例应被视为例示性而不是限制性的。因此，本发明的范围是由所附的权利要求，而不是根据之前的这些描述进行确定。在权利要求的字面意义及等同范围内的任何改变都应属于这些权利要求的范围。The concepts described herein may be embodied in other forms without departing from the spirit and scope. The specific embodiments disclosed are to be considered as illustrative and not restrictive. Therefore, the scope of the invention is to be determined by the appended claims Any changes which come within the meaning and range of the claims are intended to be within the scope of the claims.
Claims (9)
- 一种燃气轮机启动装置，用于启动燃气轮机，包括定子和相对于所述定子转动的转子，其特征在于，所述转子包括转轴以及固定至所述转轴的永磁体，所述转子的转轴与所述燃气轮机的主轴固定连接使得所述转轴能够与所述主轴同轴旋转，所述定子环绕所述转轴并设置成能够相对于所述转轴轴向移动，在所述燃气轮机启动过程中，所述定子位于与所述转轴在径向上正对的位置，当所述燃气轮机的主轴转速超过一预定转速后，所述定子轴向移动至所述转轴的径向范围之外。A gas turbine starting device for starting a gas turbine, comprising a stator and a rotor rotating relative to the stator, wherein the rotor includes a rotating shaft and a permanent magnet fixed to the rotating shaft, a rotating shaft of the rotor and the rotor The spindle fixed connection of the gas turbine enables the rotating shaft to rotate coaxially with the spindle, the stator surrounding the rotating shaft and being arranged to be axially movable relative to the rotating shaft, the stator being located during the starting of the gas turbine In a position facing the radial direction of the rotating shaft, when the rotational speed of the main shaft of the gas turbine exceeds a predetermined rotational speed, the stator axially moves out of the radial range of the rotating shaft.
- 如权利要求1所述的燃气轮机启动装置，其特征在于，所述转子的转轴为固定连接至所述燃气轮机主轴的单独元件，所述转轴与所述主轴直驱结合。A gas turbine starting device according to claim 1, wherein said rotor shaft is a separate member fixedly coupled to said gas turbine main shaft, said shaft being coupled to said spindle direct drive.
- 如权利要求1所述的燃气轮机启动装置，其特征在于，所述转子的转轴作为所述燃气轮机主轴的一部分与所述主轴一体成型。A gas turbine starting device according to claim 1, wherein a rotating shaft of said rotor is integrally formed with said main shaft as a part of said main shaft of said gas turbine.
- 如权利要求1所述的燃气轮机启动装置，其特征在于，所述预定转速为所述燃气轮机的自持转速。A gas turbine starting device according to claim 1, wherein said predetermined rotational speed is a self-sustaining rotational speed of said gas turbine.
- 一种燃气轮机，包括燃气轮机主轴，与所述燃气轮机主轴固定连接的压气机和透平以及连接在所述压气机和透平之间的燃烧室，所述燃气轮机还包括启动装置，所述启动装置包括定子和相对于所述定子转动的转子，其特征在于，所述转子包括转轴以及固定至所述转轴的永磁体，所述转子的转轴与所述燃气轮机的主轴固定连接使得所述转轴能够与所述主轴同轴旋转，所述定子环绕所述转轴并设置成能够相对于所述转轴轴向移动，在所述燃气轮机启动过程中，所述定子位于与所述转轴在径向上正对的位置，当所述燃气轮机的主轴转速超过一预定转速后，所述定子轴向移动至所述转轴的径向范围之外。A gas turbine includes a gas turbine main shaft, a compressor and a turbine fixedly coupled to the gas turbine main shaft, and a combustion chamber connected between the compressor and the turbine, the gas turbine further including a starting device, the starting device including a stator and a rotor rotating relative to the stator, wherein the rotor includes a rotating shaft and a permanent magnet fixed to the rotating shaft, and a rotating shaft of the rotor is fixedly coupled with a main shaft of the gas turbine such that the rotating shaft can The spindle rotates coaxially, the stator surrounds the rotating shaft and is arranged to be axially movable relative to the rotating shaft. During the starting of the gas turbine, the stator is located in a position orthogonal to the rotating shaft in a radial direction. When the spindle speed of the gas turbine exceeds a predetermined speed, the stator moves axially out of the radial extent of the shaft.
- 如权利要求5所述的燃气轮机，其特征在于，所述转子的转轴为固定连接至所述燃气轮机主轴的单独元件，所述转轴与所述主轴直驱结合。A gas turbine according to claim 5, wherein said rotating shaft of said rotor is a separate member fixedly coupled to said main shaft of said gas turbine, said rotating shaft being coupled to said direct drive of said main shaft.
- 如权利要求5所述的燃气轮机，其特征在于，所述转子的转轴作为所述燃气轮机主轴的一部分与所述主轴一体成型。A gas turbine according to claim 5, wherein a rotating shaft of said rotor is integrally formed with said main shaft as a part of said main shaft of said gas turbine.
- 如权利要求7所述的燃气轮机，其特征在于，所述转子的转轴自所述燃气轮机主轴一体地延伸而突出于所述压气机的端面。A gas turbine according to claim 7, wherein a rotating shaft of said rotor extends integrally from said gas turbine main shaft to protrude from an end surface of said compressor.
- 如权利要求5所述的燃气轮机，其特征在于，所述预定转速为所述燃气轮机的自持转速。A gas turbine according to claim 5, wherein said predetermined rotational speed is a self-sustaining rotational speed of said gas turbine.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| PCT/CN2015/087692 WO2017028316A1 (en) | 2015-08-20 | 2015-08-20 | Gas turbine and starting device thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| PCT/CN2015/087692 WO2017028316A1 (en) | 2015-08-20 | 2015-08-20 | Gas turbine and starting device thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| WO2017028316A1 true WO2017028316A1 (en) | 2017-02-23 |
Family
ID=58051009
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| PCT/CN2015/087692 WO2017028316A1 (en) | 2015-08-20 | 2015-08-20 | Gas turbine and starting device thereof |
Country Status (1)
| Country | Link |
|---|---|
| WO (1) | WO2017028316A1 (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112282940A (en) * | 2020-10-28 | 2021-01-29 | 郭瑞君 | Combustion engine starting device and system |
| CN114576016A (en) * | 2022-03-29 | 2022-06-03 | 清航空天(北京)科技有限公司 | Turbojet engine and starting device thereof |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB430812A (en) * | 1934-03-03 | 1935-06-25 | Bauer Eugen Gmbh | Improvements relating to electric motor driven clutch mechanisms |
| CN101100958A (en) * | 2007-07-10 | 2008-01-09 | 刘天成 | Mini size gas turbine |
| DE102006036986A1 (en) * | 2006-08-08 | 2008-02-14 | Volkswagen Ag | Electric synchronous motor with field suppressor e.g. for hybrid-drive motor vehicle, has axially movable stator so that active length of coil in magnetic exciter-field can be varied |
| CN201167292Y (en) * | 2008-03-11 | 2008-12-17 | 廖德平 | Permanent magnetic power motor |
| CN201428517Y (en) * | 2009-06-03 | 2010-03-24 | 中国航空动力机械研究所 | Auxiliary power device |
| CN103195582A (en) * | 2012-01-09 | 2013-07-10 | 霍尼韦尔国际公司 | Engine systems with enhanced start control schedules |
| CN204827675U (en) * | 2015-08-20 | 2015-12-02 | 深圳智慧能源技术有限公司 | Gas turbine and starting drive thereof |
| CN105156216A (en) * | 2015-08-20 | 2015-12-16 | 深圳智慧能源技术有限公司 | Gas turbine and starting device thereof |
-
2015
- 2015-08-20 WO PCT/CN2015/087692 patent/WO2017028316A1/en active Application Filing
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB430812A (en) * | 1934-03-03 | 1935-06-25 | Bauer Eugen Gmbh | Improvements relating to electric motor driven clutch mechanisms |
| DE102006036986A1 (en) * | 2006-08-08 | 2008-02-14 | Volkswagen Ag | Electric synchronous motor with field suppressor e.g. for hybrid-drive motor vehicle, has axially movable stator so that active length of coil in magnetic exciter-field can be varied |
| CN101100958A (en) * | 2007-07-10 | 2008-01-09 | 刘天成 | Mini size gas turbine |
| CN201167292Y (en) * | 2008-03-11 | 2008-12-17 | 廖德平 | Permanent magnetic power motor |
| CN201428517Y (en) * | 2009-06-03 | 2010-03-24 | 中国航空动力机械研究所 | Auxiliary power device |
| CN103195582A (en) * | 2012-01-09 | 2013-07-10 | 霍尼韦尔国际公司 | Engine systems with enhanced start control schedules |
| CN204827675U (en) * | 2015-08-20 | 2015-12-02 | 深圳智慧能源技术有限公司 | Gas turbine and starting drive thereof |
| CN105156216A (en) * | 2015-08-20 | 2015-12-16 | 深圳智慧能源技术有限公司 | Gas turbine and starting device thereof |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112282940A (en) * | 2020-10-28 | 2021-01-29 | 郭瑞君 | Combustion engine starting device and system |
| CN114576016A (en) * | 2022-03-29 | 2022-06-03 | 清航空天(北京)科技有限公司 | Turbojet engine and starting device thereof |
| CN114576016B (en) * | 2022-03-29 | 2024-08-02 | 清航空天(北京)科技有限公司 | Turbojet engine and starting device thereof |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US6305169B1 (en) | Motor assisted turbocharger | |
| CN105156216B (en) | Gas turbine and starting device thereof | |
| DE50107804D1 (en) | POWER GENERATOR FROM DRIVE MOTOR AND GENERATOR | |
| JPH03115739A (en) | Turbocharger with rotary electric machine | |
| AU2003217963A1 (en) | Brushless permanent magnet motor or alternator with variable axial rotor/stator alignment to increase speed capability | |
| US9695743B2 (en) | Device for driving an ancillary unit of an internal combustion engine | |
| JP2007077990A5 (en) | ||
| EP3575573A1 (en) | Hybrid amplification of high spool motoring via low spool power extraction and motoring of a differential geared generator | |
| WO2017028316A1 (en) | Gas turbine and starting device thereof | |
| KR20150081309A (en) | Method for joining bearing housing segments of a turbocharger incorporating an electric motor | |
| WO2013029480A1 (en) | Starting generator for micro turbojet engine or turbocharger | |
| HUP0302988A2 (en) | Starter | |
| CN202172349U (en) | Hybrid excitation motor apparatus | |
| CN204827675U (en) | Gas turbine and starting drive thereof | |
| CN201430501Y (en) | External mesh type electric motor | |
| CN104767331A (en) | Stator-movable type self-speed-regulating permanent magnet motor | |
| CN108999736A (en) | A kind of diesel engine drag reduction starting device | |
| WO2017028318A1 (en) | Gas turbine and starter-generator structure thereof | |
| RU2358120C1 (en) | Turbopropeller gas-turbine engine | |
| WO2020123346A3 (en) | Multi-function damper | |
| CN110107403A (en) | Integrated inspiration system built in a kind of Micro Turbine Jet Engine | |
| JP2010196586A (en) | Start control device for internal combustion engine | |
| RU2358138C1 (en) | Helical fan aviation gas-turbine engine | |
| RU2099556C1 (en) | Rotor engine | |
| KR101957987B1 (en) | Magnet generator operating in vacuum |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| 121 | Ep: the epo has been informed by wipo that ep was designated in this application |
Ref document number: 15901520 Country of ref document: EP Kind code of ref document: A1 |
|
| NENP | Non-entry into the national phase |
Ref country code: DE |
|
| 32PN | Ep: public notification in the ep bulletin as address of the adressee cannot be established |
Free format text: NOTING OF LOSS OF RIGHTS PURSUANT TO RULE 112(1) EPC (EPO FORM 1205N DATED 20/09/2018) |
|
| 122 | Ep: pct application non-entry in european phase |
Ref document number: 15901520 Country of ref document: EP Kind code of ref document: A1 |