WO2022105206A1 - 平衡轴向力的多推力盘燃气轮机 - Google Patents

平衡轴向力的多推力盘燃气轮机 Download PDF

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Publication number
WO2022105206A1
WO2022105206A1 PCT/CN2021/099959 CN2021099959W WO2022105206A1 WO 2022105206 A1 WO2022105206 A1 WO 2022105206A1 CN 2021099959 W CN2021099959 W CN 2021099959W WO 2022105206 A1 WO2022105206 A1 WO 2022105206A1
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thrust
bearing
turbine
axial force
rotating shaft
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PCT/CN2021/099959
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English (en)
French (fr)
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靳新中
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至玥腾风科技集团有限公司
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Publication of WO2022105206A1 publication Critical patent/WO2022105206A1/zh

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    • 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
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • 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
    • F02C7/06—Arrangements of bearings; Lubricating
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
    • F04D29/662—Balancing of rotors

Definitions

  • the invention relates to a multi-thrust disk gas turbine with balanced axial force, and relates to the field of axial force of gas turbines.
  • Industrial gas turbines mainly include three components: compressor, combustion chamber and turbine. After the air enters the compressor, it is compressed into high temperature and high pressure air, and then supplied to the combustion chamber for fuel combustion. During the operation of the gas turbine, the airflow will produce an axial force on the rotor blades and the disc, thereby generating an axial force. In order to prevent the rotor from moving in the axial direction, the thrust bearing will bear the axial force from the gas turbine rotor. .
  • the axial force on the gas turbine compressor rotor is forward, while the axial force on the turbine rotor is backward.
  • the compressor rotor of a certain type of gas turbine generator needs to bear a forward axial force of 510kN, and the turbine rotor needs to bear a backward axial force of 226.5kN.
  • the supporting parts of the rotor of the compressor and the rotor of the turbine need to bear a huge axial force, even if the two opposite axial forces on the rotor after the compressor rotor and the turbine rotor are integrated into one body offset each other. is still a considerable forward axial force. Therefore, a decompression device must be installed on the compressor to reduce the axial load of the rotor acting on the thrust bearing.
  • the present invention provides a multi-thrust disk gas turbine that balances the axial force.
  • a multi-thrust disk gas turbine capable of balancing axial force, comprising a rotating shaft, a compressor, a front radial bearing, at least one thrust disk and a thrust bearing, a rear radial bearing and a turbine are arranged in sequence on the rotating shaft, and the rotating shaft and each bearing cover are provided with Stator, an air inlet is arranged around the outer side of the stator, the air inlet contains an inner wall and an outer wall, the end of the air inlet is connected to the combustion chamber, and the outlet of the combustion chamber faces the blade edge of the front end face of the turbine;
  • a front air seal is arranged in the gap between the rear end face of the compressor and the front side of the stator, so as to reduce the leakage of gas from the edge of the compressor to its back side;
  • a rear gas seal is arranged between the front end of the turbine turbine and the outlet of the combustion chamber, which is used to reduce the leakage of the gas ejected from the combustion chamber to the front end of the turbine;
  • the thrust bearing arranged on the front side of the thrust disc is used to bear the thrust of the front end face of the thrust disc;
  • a first bearing air seal is arranged between the thrust plate and the end face of the stator to reduce gas leakage in the direction of the compressor; a second bearing air seal is arranged between the curved surface of the inner ring of the stator and the rotating shaft to reduce leakage in the direction of the turbine and a pressure relief channel is opened between the first bearing air seal and the second bearing air seal to reduce the pressure on the rear end surface of the thrust plate.
  • the compressor is fixedly connected with the rotating shaft;
  • the turbine is fixedly connected with the rotating shaft;
  • the thrust plate is fixedly connected or integrally formed with the rotating shaft;
  • the front radial bearing and the rear radial bearing are both air bearings, sleeved on the rotating shaft;
  • the bearing is sleeved on the rotating shaft and the thrust surface is in contact with the front end of the thrust plate.
  • the thrust bearing includes two parts: one part is arranged at the front end of the front thrust disk, and the two ends are respectively It is in contact with the end face of the stator and the front end face of the front thrust disc; the other part is arranged between the two thrust discs, and the two end faces are respectively in contact with the rear end surface of the front thrust disc and the front end surface of the rear thrust disc.
  • the force surface of the thrust disc is both for the front face.
  • the front air seal, the rear air seal, the first bearing air seal and the second bearing air seal are all staggered tooth air seals or grate tooth air seals.
  • the gas passes through the laminar flow and crosses the comb teeth, and the gas changes from laminar flow to turbulent flow, which reduces the flow rate and reduces the pressure.
  • the front air seal reduces the gas leaking to the rear end of the compressor and reduces the air pressure, and the thrust received at the back of the compressor is reduced or even disappears;
  • the rear air seal reduces leakage to permeability
  • the gas at the flat front end reduces the air pressure, and the thrust on the front side of the turbine decreases or even disappears;
  • the first bearing air seal, the second bearing air seal and the pressure relief passage reduce the pressure on the right side of the thrust plate, due to the high pressure at one end of the compressor , the front end face of the thrust disc bears part of the thrust generated when the rotor rotates, so it is guaranteed that the thrust disc will not receive the thrust on the right side, and the thrust disc only needs to bear the pressure of the front end face.
  • two thrust discs are arranged, so that the force received by each thrust disc is reduced by half after sharing the axial force, which can prolong the service life.
  • the number of thrust discs can also be set to one or more than two, and the number of thrust discs can be selected according to the magnitude of the axial force. The greater the axial force, the more thrust discs.
  • the multi-thrust disc gas turbine with balanced axial force of the present invention adopts the multi-air seal sealing design, which can reduce leakage more and at the same time can effectively overcome the disadvantage of unstable sealing performance caused by the vibration of the unit; It can effectively reduce the axial force, increase the stability of the unit, reduce power consumption, and improve efficiency; and there are no wearing parts, which can prolong the life of the unit.
  • FIG. 1 is a schematic structural diagram of the present invention.
  • FIG. 2 is a partial enlarged view of position A in FIG. 1 .
  • a multi-thrust disk gas turbine for balancing axial force including a rotating shaft 1, on which a compressor 2, a front radial bearing 61, a thrust bearing 62, a thrust disk 11, a rear radial bearing 63 and a turbine 3 are arranged in sequence, such as As shown in Figures 1 and 2, the compressor 2 is fixedly connected with the rotating shaft 1; the turbine 3 is fixedly connected with the rotating shaft 1; the thrust plate 11 is fixedly connected or integrally formed with the rotating shaft 1; the front radial bearing 61 and the rear radial bearing 63 are both The air bearing is sleeved on the rotating shaft 1 ; the thrust bearing 62 is sleeved on the rotating shaft 1 and the thrust surface is in contact with the front end of the thrust plate 11 .
  • the rotating shaft 1 and each bearing cover set the sub-4, the stator 4 is surrounded by an air inlet 51, the air inlet 51 contains an inner wall and an outer wall, the end of the air inlet 51 is connected to the combustion chamber 5, and the outlet of the combustion chamber 5 faces the turbine 3 Frontal leaf margin.
  • a front air seal 71 is arranged in the gap between the rear end surface of the compressor 2 and the front side of the stator 4 to reduce the leakage of air from the edge of the compressor 2 to the back surface thereof.
  • a rear gas seal 72 is arranged between the front end of the turbine of the turbine 3 and the outlet of the combustion chamber 5 to reduce the leakage of the gas ejected from the combustion chamber 5 to the front end of the turbine 3 .
  • a thrust bearing 62 is provided on the front side of the thrust plate 11 to bear the thrust of the front end surface of the thrust plate 11 .
  • a first bearing air seal 73 is arranged between the thrust plate 11 and the end face of the stator to reduce the gas leakage in the direction of the compressor 2; a second bearing air seal 74 is arranged between the inner ring surface of the stator 4 and the rotating shaft 1 to reduce the The gas leaking in the direction of the turbine 3; and a pressure relief channel 8 is opened between the first bearing air seal 73 and the second bearing air seal 74, so that the pressure on the rear end surface of the thrust plate 11 is reduced.
  • the thrust discs 11 are provided in two, respectively the front thrust disc (near the compressor 1) and the rear thrust disc (near the turbine 3);
  • the thrust bearing 62 includes two parts: one part is arranged at the front end of the front thrust disc, the other The end faces are respectively in contact with the end face of the stator 4 and the front end face of the front thrust disc; the other part is arranged between the two thrust discs, and the two end faces are respectively in contact with the rear end face of the front thrust disc and the front end face of the rear thrust disc.
  • the force surface is the front surface.
  • the front air seal 71 , the rear air seal 72 , the first bearing air seal 73 and the second bearing air seal 74 are staggered tooth air seals or grate tooth air seals.
  • the gas passes through the laminar flow and crosses the comb teeth, and the gas changes from laminar flow to turbulent flow, which reduces the flow rate and reduces the pressure.
  • the front air seal 71 reduces the gas leaking to the rear end of the compressor 2 and reduces the air pressure, the thrust on the back of the compressor 2 is reduced or even disappears; the rear air seal 72 reduces The gas leaked to the front end of the turbine 3 is reduced, the air pressure is reduced, and the thrust on the front side of the turbine 3 is reduced or even disappears; the first bearing air seal 73, the second bearing air seal 74 and the pressure relief passage The side pressure is reduced.
  • the present invention can effectively reduce the axial force, increase the stability of the unit, reduce the power consumption, and improve the efficiency; the multi-air seal design can reduce leakage even more, and there are no wearing parts, and at the same time, it can effectively overcome the vibration caused by the unit.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

一种平衡轴向力的多推力盘燃气轮机，包括转轴（1），转轴（1）上依次设置有压气机（2）、前径向轴承（61）、多个推力盘（11）及推力轴承（62）、后径向轴承（63）和透平（3）；转轴（1）及各轴承外罩设定子（4），定子外侧环绕设置进气道（51），进气道（51）末端连接燃烧室（5），燃烧室（5）出口朝向透平（3）前端面叶缘；压气机（2）后端面和定子（4）前侧之间的间隙内设置前气封；透平（3）涡轮前端与燃烧室（5）出口之间设置后气封；推力盘（11）和定子（4）端面之间设置第一轴承气封（71）；定子（4）内圈曲面和转轴（1）之间设置第二轴承气封（72），在第一轴承气封（71）和第二轴承气封（72）之间开设泄压通道。采用多气封密封设计，能够降低泄漏、克服机组震动带来的密封性能不稳定的缺点；采用多推力盘分摊轴向力，能够降低轴向力、增加机组稳定性、降低功耗。

Description

平衡轴向力的多推力盘燃气轮机 技术领域
本发明涉及一种平衡轴向力的多推力盘燃气轮机，涉及燃气轮机的轴向力领域。
背景技术
工业燃气轮机主要包括压气机、燃烧室及透平三大部件。空气进入压气机后被压缩成高温高压的空气，然后供给燃烧室燃料燃烧，其产生的高温高压燃气在透平中膨胀做功。燃气轮机在运行过程中，气流会对转子叶片及轮盘产生轴向力作用，从而产生轴向上的力，而为了防止转子发生轴向上的移动，推力轴承会承受来自燃气轮机转子的轴向力。
由气体动力学可知：燃气轮机压气机转子上的轴向力是向前的，而涡轮转子上的轴向力是向后的。例如，在最大工况下，某型燃气轮机发生器上压气机转子需要承受510kN向前的轴向力，涡轮转子需要承受226.5kN向后的轴向力。由此可知，压气机的转子和涡轮的转子的支承部分需要承受巨大的轴向力，即便压气机转子和涡轮转子连成一体后转子上的两个方向相反的轴向力相互抵消了一部分，仍是一个数值相当大的向前的轴向力。因此，必须在压气机上设置减荷装置，用以减少转子作用在止推轴承上的轴向负荷。
发明内容
针对上述现有技术，本发明提供了一种平衡轴向力的多推力盘燃气轮机。
本发明是通过以下技术方案实现的：
一种平衡轴向力的多推力盘燃气轮机，包括转轴，转轴上依次设置有压气机、前径向轴承、至少一个推力盘及推力轴承、后径向轴承和透平，转轴及各轴承外罩设定子，定子外侧环绕设置进气道，进气道含有内壁和外壁，进气道末端连接燃烧室，燃烧室出口朝向透平前端面叶缘；
所述压气机后端面和定子前侧之间的间隙内设置前气封，用于减少压气机边缘气体泄漏流至其背面；
所述透平涡轮前端与燃烧室出口之间设置后气封，用于减少燃烧室喷出的气体泄漏至透平的前端；
所述推力盘前侧设置的推力轴承，用以承受推力盘前端面的推力；
所述推力盘和定子端面之间设置第一轴承气封，用于减少压气机方向泄漏的气体；所述定子内圈曲面和转轴之间设置第二轴承气封，用于减少透平方向泄漏的气体，且在第一轴承 气封和第二轴承气封之间开设泄压通道，使推力盘后端面压力减小。
进一步的，所述压气机与转轴固定连接；透平与转轴固定连接；推力盘与转轴固定连接或一体成型；前径向轴承、后径向轴承均为空气轴承，套设在转轴上；推力轴承套设在转轴上且推力面与推力盘前端相抵。
进一步的，所述推力盘为两个：分别为前推力盘(靠近压气机)和后推力盘(靠近透平)；推力轴承包括两部分：其中一部分设置在前推力盘的前端，两端面分别与定子端面和前推力盘前端面相抵；另一部分设置在两推力盘之间，两端面分别与前推力盘的后端面、后推力盘的前端面相抵，转子转动时推力盘的受力面均为前端面。
进一步的，所述前气封、后气封、第一轴承气封及第二轴承气封，均为交错齿气封或篦齿气封。气体通过层流的方式，越过梳齿，气体由层流变成紊流，降低了流速，使得压力降低。
本发明的平衡轴向力的多推力盘燃气轮机，由于前气封减少了泄漏至压气机后端的气体、降低了气压，压气机背后受到的推力减小甚至消失；后气封减少了泄漏至透平前端的气体、降低了气压，透平前侧受到的推力减小甚至消失；第一轴承气封和第二轴承气封及泄压通道使推力盘右侧压力降低，由于压气机一端压力高，推力盘前端面承受了转子转动时产生的部分推力，所以保障了推力盘不会受到右侧推力，推力盘仅需承受前侧端面的压力。本发明将推力盘设置为两个，则每个推力盘分担轴向力后受力减少一半，可延长使用寿命。
具体应用时，推力盘数量还可以设置为一个或两个以上，可根据轴向力大小选择推力盘个数，轴向力越大，推力盘越多。
本发明的平衡轴向力的多推力盘燃气轮机，采用多气封密封设计，可以更小的降低泄漏，同时能有效克服机组震动带来的密封性能不稳定的缺点；采用多推力盘分摊轴向力，可有效降低轴向力，增加机组稳定性，降低功耗，提升效率；而且没有易损件，可延长机组寿命。
本发明使用的各种术语和短语具有本领域技术人员公知的一般含义。提及的术语和短语如有与公知含义不一致的，以本发明所表述的含义为准。
附图说明
图1为本发明的结构示意图。
图2是图1中A位置局部放大图。
其中，1-转轴，11-推力盘，2-压气机，3-透平，4-定子，5-燃烧室，51-进气道，61-前径向轴承，62-推力轴承，63-后径向轴承，71-前气封，72-后气封，73-第一轴承气封，74-第二轴承气封，8-泄压通道。
具体实施方式
下面结合附图对本发明作进一步的说明。然而，本发明的范围并不限于下述实施例。本领域的专业人员能够理解，在不背离本发明的精神和范围的前提下，可以对本发明进行各种变化和修饰。
一种平衡轴向力的多推力盘燃气轮机，包括转轴1，转轴1上依次设置压气机2、前径向轴承61、推力轴承62及推力盘11、后径向轴承63和透平3，如图1、图2所示，压气机2与转轴1固定连接；透平3与转轴1固定连接；推力盘11与转轴1固定连接或一体成型；前径向轴承61、后径向轴承63均为空气轴承，套设在转轴1上；推力轴承62套设在转轴1上且推力面与推力盘11前端相抵。
所述转轴1及各轴承外罩设定子4，定子4外侧环绕设置进气道51，进气道51含有内壁和外壁，进气道51末端连接燃烧室5，燃烧室5出口朝向透平3前端面叶缘。
所述压气机2后端面和定子4前侧之间的间隙内设置前气封71，用于减少压气机2边缘气体泄漏流至其背面。
所述透平3涡轮前端与燃烧室5出口之间设置后气封72，用于减少燃烧室5喷出的气体泄漏至透平3的前端。
所述推力盘11前侧设置推力轴承62，用以承受推力盘11前端面的推力。
所述推力盘11和定子端面之间设置第一轴承气封73，用于减少压气机2方向泄漏的气体；定子4内圈曲面和转轴1之间设置第二轴承气封74，用于减少透平3方向泄漏的气体；且在第一轴承气封73和第二轴承气封74之间开设泄压通道8，使推力盘11后端面压力减小。
所述推力盘11设置为两个，分别为前推力盘(靠近压气机1)和后推力盘(靠近透平3)；推力轴承62包括两部分：其中一部分设置在前推力盘的前端、两端面分别与定子4端面和前推力盘前端面相抵；另一部分设置在两推力盘之间，两端面分别与前推力盘的后端面、后推力盘的前端面相抵，转子转动时推力盘的受力面均为前端面。
所述前气封71、后气封72、第一轴承气封73及第二轴承气封74为交错齿气封或篦齿气封。气体通过层流的方式，越过梳齿，气体由层流变成紊流，降低了流速，使得压力降低。
本发明的平衡轴向力的多推力盘燃气轮机，由于前气封71减少了泄漏至压气机2后端的气体、降低了气压，压气机2背后受到的推力减小甚至消失；后气封72减少了泄漏至透平3前端的气体、降低了气压，透平3前侧受到的推力减小甚至消失；第一轴承气封73和第二轴承气封74及泄压通道8使推力盘11右侧压力降低，由于压气机2一端压力高，推力盘11前端面承受了转子转动时产生的部分推力，所以保障了推力盘11不会受到右侧推力，推力盘 11仅需承受前侧端面的压力。因此，本发明可有效降低轴向力，增加机组稳定性，降低功耗，提升效率；多气封密封设计，可以更小的降低泄漏，而且没有易损件，同时能有效克服机组震动带来的密封性能不稳定的缺点。
给本领域技术人员提供上述实施例，以完全公开和描述如何实施和使用所主张的实施方案，而不是用于限制本文公开的范围。对于本领域技术人员而言显而易见的修饰将在所附权利要求的范围内。

Claims (8)

  1. 一种平衡轴向力的多推力盘燃气轮机，其特征在于：包括转轴，转轴上依次设置有压气机、前径向轴承、至少一个推力盘及推力轴承、后径向轴承和透平；转轴及各轴承外罩设定子，定子外侧环绕设置进气道，进气道含有内壁和外壁，进气道末端连接燃烧室，燃烧室出口朝向透平前端面叶缘；
    所述压气机后端面和定子前侧之间的间隙内设置前气封；
    所述透平涡轮前端与燃烧室出口之间设置后气封；
    所述推力盘和定子端面之间设置第一轴承气封；所述定子内圈曲面和转轴之间设置第二轴承气封，且在第一轴承气封和第二轴承气封之间开设泄压通道。
  2. 根据权利要求1所述的平衡轴向力的多推力盘燃气轮机，其特征在于：所述压气机与转轴固定连接。
  3. 根据权利要求1所述的平衡轴向力的多推力盘燃气轮机，其特征在于：所述透平与转轴固定连接。
  4. 根据权利要求1所述的平衡轴向力的多推力盘燃气轮机，其特征在于：所述推力盘与转轴固定连接或一体成型。
  5. 根据权利要求1所述的平衡轴向力的多推力盘燃气轮机，其特征在于：所述前径向轴承、后径向轴承均为空气轴承，套设在转轴上。
  6. 根据权利要求1所述的平衡轴向力的多推力盘燃气轮机，其特征在于：所述推力轴承套设在转轴上且推力面与推力盘前端相抵。
  7. 根据权利要求1或4或6所述的平衡轴向力的多推力盘燃气轮机，其特征在于：所述推力盘为两个：分别为靠近压气机的前推力盘和靠近透平的后推力盘；推力轴承包括两部分：其中一部分设置在前推力盘的前端，两端面分别与定子端面和前推力盘前端面相抵；另一部分设置在两推力盘之间，两端面分别与前推力盘的后端面、后推力盘的前端面相抵，转子转动时推力盘的受力面均为前端面。
  8. 根据权利要求1所述的平衡轴向力的多推力盘燃气轮机，其特征在于：所述前气封、后气封、第一轴承气封及第二轴承气封为交错齿气封或篦齿气封。
PCT/CN2021/099959 2020-11-18 2021-06-15 平衡轴向力的多推力盘燃气轮机 WO2022105206A1 (zh)

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