CN111058945A - Miniature gas turbine - Google Patents
Miniature gas turbine Download PDFInfo
- Publication number
- CN111058945A CN111058945A CN201911370913.1A CN201911370913A CN111058945A CN 111058945 A CN111058945 A CN 111058945A CN 201911370913 A CN201911370913 A CN 201911370913A CN 111058945 A CN111058945 A CN 111058945A
- Authority
- CN
- China
- Prior art keywords
- bearing
- radial bearing
- low
- gas
- turbine
- 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
Links
Images
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
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
-
- 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
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/20—Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products
- F02C3/22—Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products the fuel or oxidant being gaseous at standard temperature and pressure
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
Abstract
The present invention provides a micro gas turbine, comprising: a high pressure machine, a low pressure machine and a heat regenerator; the high-pressure machine comprises a gas compressor, a high-pressure turbine, a combustion chamber and a high-pressure rotor system; the low-pressure machine comprises a low-pressure turbine, a motor, a low-pressure rotor system and a flue gas chamber; the gas inlet end of the gas compressor is communicated with the outside, the gas outlet end of the gas compressor is communicated with the first inlet of the heat regenerator, the first outlet of the heat regenerator is communicated with the inlet of the combustion chamber, the gas outlet end of the combustion chamber is communicated with the gas inlet end of the high-pressure turbine, the gas outlet end of the high-pressure turbine is communicated with the gas inlet end of the low-pressure turbine, the gas outlet end of the low-pressure turbine is communicated with the inlet of the gas chamber, the outlet of the gas chamber is communicated with the second inlet of the heat regenerator, and the second outlet of the heat regenerator is. The invention forms a compact micro gas turbine by reasonably matching the heat regenerator, and can fully improve the heat efficiency.
Description
Technical Field
The invention relates to the field of gas turbines, in particular to a micro gas turbine.
Background
The micro gas turbine is a small heat engine which is newly developed, the single-machine power range of the micro gas turbine is 25-300 kW, and the basic technical characteristics are that a radial-flow impeller machine and a regenerative cycle are adopted. The gas turbine generator set in the prior art has the following defects:
the regenerator of the micro gas turbine is one of the most critical components for improving the heat efficiency of the micro gas turbine, and the regenerator is a heat exchanger for exchanging heat between compressed air and high-temperature gas, and the adoption of the regenerator enables the heat efficiency of the micro gas turbine to be improved most directly, effectively and reliably. The heat efficiency of the micro gas turbine is more than 30%, the key technology is to use a heat regenerator, and if the heat regenerator is not adopted, the maximum heat efficiency of the micro gas turbine can only reach about 17%. In the prior art, different combination configuration modes of a heat regenerator and a micro gas turbine greatly influence the thermal efficiency of the micro gas turbine, and an unreasonable combination mode can cause unnecessary heat loss along the way.
Meanwhile, in the prior art, the high-speed rotor of the micro gas turbine is connected with the motor rotor to generate electricity, the rotating speed of a rotor system of the micro gas turbine exceeds 14 ten thousand RPM (revolutions per minute), the working temperature is 950 plus-1000 ℃, the working linear speed is extremely high, the bearing centrifugal force of the gas compressor and the turbine impeller is up to 100MPa, and the requirement on the bearing strength is extremely high. Under the high-speed state, because there is the axiality deviation to lead to miniature gas turbine engine set rotor system poor stability, along with the improvement of rotor rotational speed, the axial force that the rotor received can further improve, under the high rotational speed operating condition of miniature gas turbine, the rotor axial force that bears on the shaft coupling is great, leads to the shaft coupling to damage easily.
In addition, for the rotor system, the traditional installation mode that the thrust bearing is arranged between the gas compressor and the turbine is that for the whole rotor system, the thrust bearing is of a cantilever shaft type structure, and the gravity center is deviated to the side of the turbine, so that the stability of the whole rotor system is poor; meanwhile, high temperature suffered by the turbine hot end component during working can be transferred to the thrust bearing, so that the working temperature of the bearing is increased, and the effect of blocking a rotor system due to expansion and abrasion of a shaft system is easily caused; in addition, by adopting the traditional installation mode, if the thrust bearing is installed between the coupler and the air compressor, the thrust disc with large diameter has the possibility of blocking the air inlet of the micro gas turbine; if the thrust bearing is arranged on the coupler and faces the motor I, all axial force of the rotor of the micro gas turbine acts on the coupler, so that the coupler is damaged, and the problem that the thrust bearing does not have an installation position can be caused. It can be seen that the conventional layout structure of the micro gas turbine system limits the further increase of the rotation speed of the micro gas turbine.
Disclosure of Invention
In order to solve the above-mentioned problems, an object of the present invention is to provide a micro gas turbine.
The technical scheme of the invention is as follows:
a micro gas turbine, comprising:
a high pressure machine, a low pressure machine and a heat regenerator;
the high-pressure machine comprises a gas compressor, a high-pressure turbine, a combustion chamber and a high-pressure rotor system, wherein the gas compressor and the high-pressure turbine are coaxially and fixedly arranged on the high-pressure rotor system back to back;
the low-pressure machine comprises a low-pressure turbine, a motor, a low-pressure rotor system and a flue gas chamber; the low-pressure turbine and the motor are sequentially coaxially and fixedly arranged on the low-pressure rotor system;
the gas inlet end of the gas compressor is communicated with the outside, the gas outlet end of the gas compressor is communicated with the first inlet of the heat regenerator, the first outlet of the heat regenerator is communicated with the inlet of the combustion chamber, the gas outlet end of the combustion chamber is communicated with the gas inlet end of the high-pressure turbine, the gas outlet end of the high-pressure turbine is communicated with the gas inlet end of the low-pressure turbine, the gas outlet end of the low-pressure turbine is communicated with the inlet of the gas chamber, the outlet of the gas chamber is communicated with the second inlet of the heat regenerator, and the second outlet of the heat regenerator is.
Further, the air compressor is a centrifugal air compressor, and a starting motor is arranged at the front end of the air compressor.
Further, the low-pressure turbine is a centrifugal or centripetal or axial turbine;
when the low-pressure turbine is a centrifugal turbine, the small end of the low-pressure turbine and the small end of the high-pressure turbine are oppositely and non-connected;
when the low-pressure turbine is a centripetal turbine, the large end of the low-pressure turbine and the small end of the high-pressure turbine are arranged oppositely and in the same direction in a non-connected mode.
Furthermore, the combustion chamber is a rotary reflux combustion chamber or an axial flow combustion chamber, and the axis of the combustion chamber is coaxial with the installation shafts of the gas compressor and the high-pressure turbine;
the combustion chamber is arranged on one side of the high-pressure turbine far away from the compressor, or the combustion chamber is arranged between the high-pressure turbine and the compressor.
Further, the heat regenerator is arranged outside the combustion chamber in a surrounding manner;
the heat regenerator is an annular or square box body;
the heat regenerators are arranged in an integrated or split mode, and when the heat regenerators are arranged in a split mode, the heat regenerators are uniformly or non-uniformly arranged;
the first inlet and the second outlet of the heat regenerator are cold ends, and the first inlet and the second inlet are hot ends, wherein the first inlet and the first outlet form a first channel, the second inlet and the second outlet form a second channel, and the first channel and the second channel are not communicated.
Further, the heat regenerator is also provided with a third inlet and a third outlet;
the exhaust end of the high-pressure turbine is also communicated with a third inlet of the heat regenerator, and a third outlet of the heat regenerator is communicated with the air inlet end of the low-pressure turbine.
Further, the heat regenerator is arranged outside the combustion chamber in a surrounding manner;
the heat regenerator is an annular or square box body;
the heat regenerators are arranged in an integrated or split mode, and when the heat regenerators are arranged in a split mode, the heat regenerators are uniformly or non-uniformly arranged;
the first inlet, the second outlet and the third outlet of the regenerator are cold ends, and the first outlet, the second inlet and the third inlet are hot ends, wherein the first inlet and the first outlet form a first channel, the second inlet and the second outlet form a second channel, the third inlet and the third outlet form a third channel, and the first channel, the second channel and the third channel are not communicated.
Furthermore, the low-pressure rotor system comprises a turbine shaft for mounting a low-pressure turbine and a motor shaft for mounting a motor, and the turbine shaft and the motor shaft are connected through a coupling;
a first bearing and a second bearing are arranged between the low-pressure turbine and the coupler, and a motor shaft is rotatably connected with the motor body through a third bearing and a fourth bearing.
Furthermore, the low-pressure rotor system further comprises a first casing and a second casing, the first casing is connected with the second casing through a coupler, the first bearing, the second bearing and the low-pressure turbine are arranged in the first casing, and the motor, the third bearing and the fourth bearing are arranged in the second casing.
Further, the first bearing, the second bearing, the third bearing and the fourth bearing are respectively a thrust bearing, a first radial bearing, a second radial bearing and a third radial bearing, the thrust bearing is arranged between the low-pressure turbine and the coupler and close to the low-pressure turbine, the first radial bearing is arranged between the low-pressure turbine and the coupler and close to the coupler, the second radial bearing is arranged on one side of the motor close to the low-pressure turbine, and the third radial bearing is arranged on the other side of the motor far from the low-pressure turbine;
or the first bearing, the second bearing, the third bearing and the fourth bearing are respectively a first radial bearing, a thrust bearing, a second radial bearing and a third radial bearing;
the first radial bearing is arranged at a position between the low-pressure turbine and the coupler and close to the low-pressure turbine, the thrust bearing is arranged at a position between the low-pressure turbine and the coupler and close to the coupler, the second radial bearing is arranged at one side of the motor close to the low-pressure turbine, and the third radial bearing is arranged at the other side of the motor far away from the low-pressure turbine.
Further, the thrust bearing and the first radial bearing are non-contact bearings, and the second radial bearing and the third radial bearing are non-contact bearings or contact bearings.
Further, the thrust bearing adopts a gas-magnetic hybrid thrust bearing or an air thrust bearing or a magnetic bearing; the first radial bearing adopts a gas dynamic and static pressure mixed radial bearing or a gas magnetic mixed radial bearing, and the second radial bearing and the third radial bearing both adopt a gas dynamic and static pressure mixed radial bearing or a gas magnetic mixed radial bearing or a ball bearing.
Further, the thrust bearing and the first radial bearing are arranged to be an integrated bearing;
the integrated bearing includes:
the thrust disc is fixedly connected with the turbine shaft or integrally formed;
the first bearing body and the second bearing body are sleeved on the turbine shaft and positioned on two sides of the thrust disc;
wherein the first bearing body has a radial bearing portion and a thrust bearing portion which are integrally formed, the radial bearing portion having a predetermined radial clearance in a radial direction from the turbine shaft so as to form the first radial bearing;
the thrust bearing portion is mounted axially opposite the thrust disk with a predetermined first axial gap, and the second bearing body is mounted axially opposite the thrust disk with a predetermined second axial gap, thereby forming the thrust bearing.
Further, first bearing, second bearing, third bearing, fourth bearing are first journal bearing, second journal bearing, third journal bearing and fourth journal bearing respectively, first journal bearing sets up the position that is close to the low-pressure turbine between low-pressure turbine and shaft coupling, second journal bearing sets up the position that is close to the shaft coupling between low-pressure turbine and shaft coupling, third journal bearing sets up and is close to low-pressure turbine one side in the motor, fourth journal bearing sets up the opposite side that the low-pressure turbine was kept away from to the motor.
Further, the first radial bearing and the second radial bearing are both contact bearings, and the third radial bearing and the fourth radial bearing are non-contact bearings or contact bearings.
Further, the first radial bearing and the second radial bearing both adopt ball bearings, and the third radial bearing and the fourth radial bearing both adopt a gas hybrid dynamic and static pressure radial bearing or a gas-magnetic hybrid radial bearing or a ball bearing.
Further, low pressure rotor system includes the low pressure pivot, low pressure pivot formula pivot as an organic whole, low pressure turbine and motor install in the low pressure pivot, be provided with first bearing, second bearing between low pressure turbine and the motor, the motor is kept away from low pressure turbine one side and is provided with the third bearing.
Further, the first bearing, the second bearing and the third bearing are respectively a thrust bearing, a first radial bearing and a second radial bearing;
or, the first bearing, the second bearing and the third bearing are respectively a first radial bearing, a thrust bearing and a second radial bearing.
Further, the thrust bearing and the first radial bearing are both non-contact bearings, and the second radial bearing is a non-contact bearing or a contact bearing.
Further, the thrust bearing adopts a gas-magnetic hybrid thrust bearing or a gas thrust bearing or a magnetic bearing, the first radial bearing adopts a gas-dynamic-static hybrid radial bearing or a gas-magnetic hybrid radial bearing, and the second radial bearing adopts a gas-dynamic-static hybrid radial bearing or a gas-magnetic hybrid radial bearing or a ball bearing.
Further, the first bearing, the second bearing and the third bearing are respectively a first radial bearing, a second radial bearing and a third radial bearing.
Further, the first radial bearing and the second radial bearing are both contact bearings, and the third radial bearing is a non-contact bearing or a contact bearing.
Furthermore, ball bearings are adopted by the first radial bearing and the second radial bearing, and a gas dynamic and static pressure mixed radial bearing or a gas magnetic mixed radial bearing or a ball bearing is adopted by the third radial bearing.
Compared with the prior art, the invention has the following beneficial effects:
1. the heat regenerator is reasonably matched, so that the heat efficiency is fully improved, the heat loss along the way is small, the structure is compact, and the integration level with a gas turbine is high; in the invention, the high-pressure rotor system and the low-pressure rotor system are short in shaft system, and the requirements on the rotor dynamics of the two shaft systems are low.
2. In the low-pressure rotor system structure provided by the invention, the stable operation of the gas turbine can be ensured; the requirement of the bearing peak value (rotating speed multiplied by diameter) is reduced, the freedom degree of selecting the bearing is large, and the free combination of the ball bearing and the air bearing can meet the work.
3. The high-pressure machine and the low-pressure machine can be spliced and disassembled in a modularized mode, the requirement on the assembly and matching relationship between the two modules is low, the damaged parts (such as bearings and sealing parts) can be maintained and replaced conveniently, the maintenance is convenient, and the flexibility is good.
4. The micro gas turbine provided by the invention can realize power generation and supply through the high-voltage machine and the low-voltage machine, can realize heat supply through the heat regenerator, can integrally realize combined heat and power supply/combined cold and power supply, is stable and reliable in switching among various functions, can be combined in a random mode, and has obvious advantages in application scenes.
Drawings
FIG. 1 is an overall block diagram of a micro gas turbine according to an embodiment.
FIG. 2 is an overall configuration diagram of a micro gas turbine according to a first embodiment.
FIG. 3 is a schematic structural view of a medium-high pressure machine according to an embodiment.
FIG. 4 is a schematic structural view of a middle/low-pressure machine according to an embodiment.
Fig. 5 is a schematic structural diagram of a regenerator in the second embodiment.
Fig. 6 is a schematic view of a low-medium-pressure rotor system according to a third embodiment.
Fig. 7 is a schematic view of a low-medium pressure rotor system in the third embodiment.
Fig. 8 is a structural view of an integrated gas bearing of the present invention.
Fig. 9 is a front view of the first bearing body of the present invention.
FIG. 10 is a left side view of the first bearing body of the present invention.
Fig. 11 is a third schematic view of a third middle-low pressure rotor system according to the third embodiment.
Fig. 12 is a schematic view of a fourth low-medium pressure rotor system according to the first embodiment.
Fig. 13 is a second schematic view of a low-medium pressure rotor system according to a fourth embodiment.
Fig. 14 is a schematic view of a fourth medium-low pressure rotor system of the embodiment.
Detailed Description
In order to better understand the technical scheme of the invention, the invention is further explained by combining the specific embodiment and the attached drawings of the specification.
Example one
As shown in fig. 1, 2, 3, and 4, the embodiment provides a micro gas turbine with a regenerator, which includes a high-pressure machine 1, a low-pressure machine 2, and a regenerator 3, where the high-pressure machine 1 includes a compressor 11, a high-pressure turbine 12, a combustion chamber 13, a first rotating shaft 14, and a high-pressure bearing set 15, the low-pressure machine 2 includes a low-pressure turbine 21, a motor 22, a low-pressure bearing set 24, a second rotating shaft 23, and a flue gas chamber 25, and the regenerator 3 has a first inlet 31, a first outlet 32, a second inlet 33, and a second outlet 34.
In this embodiment, the compressor 11 and the high-pressure turbine 12 are coaxially and fixedly mounted on the first rotating shaft 14 back to back, the air inlet end of the compressor 11 is communicated with the outside, the air outlet end is communicated with the first inlet 31 of the regenerator, the first outlet 32 of the regenerator is communicated with the inlet of the combustion chamber 13, the air outlet end of the combustion chamber 13 is communicated with the air inlet end of the high-pressure turbine 12, the air outlet end of the high-pressure turbine 12 is communicated with the air inlet end of the low-pressure turbine 21, and the exhaust gas of the high-pressure compressor 11 enters the regenerator 3 for heat exchange and temperature rise and then enters the combustion chamber 13. The flue gas chamber 25 is arranged on one side of the low-pressure turbine 21, an inlet of the flue gas chamber 25 is communicated with an exhaust end of the low-pressure turbine 21, an outlet of the flue gas chamber 25 is communicated with a second inlet 33 of the heat regenerator in a butt joint mode, a second outlet 34 of the heat regenerator is communicated with the outside, gas at an outlet of the flue gas chamber 25 is discharged outside after being subjected to heat exchange and cooling, the outlet of the flue gas chamber 25 can be square or in other shapes, and the second outlet 34 of the heat regenerator is communicated with the outside.
In this embodiment, the first inlet 31 and the second outlet 34 of the regenerator are cold ends, the first outlet 32 and the second inlet 33 are hot ends, the first inlet 31 and the first outlet 32 form a first channel, the second inlet 33 and the second outlet 34 form a second channel, and the first channel and the second channel are not communicated with each other.
In this embodiment, the flow direction of the micro gas turbine is as follows: the gas firstly enters the gas compressor 11, enters the hot end inlet of the heat regenerator 3 after being pressurized by the gas compressor 11, is heated into high-temperature and high-pressure gas through heat exchange in the heat regenerator 3, then enters the inlet of the combustion chamber 13, is combusted in the combustion chamber 13 to generate high-temperature gas, the high-temperature gas is ejected from the outlet of the combustion chamber 13 to push the high-pressure turbine 12 to rotate, expand and do work, because the high-pressure turbine 12 is coaxially connected with the gas compressor 11, the high-pressure turbine 12 rotates to further drive the gas compressor 11 to rotate, gas enters the inlet of the flue gas chamber 25, high-temperature tail gas enters the inlet of the flue gas chamber 25 to directly push the low-pressure turbine 21 in the flue gas chamber 25 to rotate at a high speed, the shaft of the low-pressure turbine 21 drives the motor 22 to generate.
Preferably, the high-pressure compressor 11 is a centrifugal compressor, and a starting motor is arranged at the front end of the compressor 11.
Preferably, the low pressure turbine 21 and the motor 22 are coaxially and fixedly mounted on the second rotating shaft 23 in sequence, the low pressure turbine 21 is a centrifugal turbine, a centripetal turbine or an axial turbine, when the low pressure turbine 21 is a centrifugal turbine, the small end of the low pressure turbine 21 and the small end of the high pressure turbine 12 are oppositely and non-connected, the small end of the low pressure turbine 21 is arranged adjacent to the high pressure machine 1, the large end of the low pressure turbine 21 and the motor 22 are arranged adjacent, when the low pressure turbine 21 is a centripetal turbine, the large end of the low pressure turbine 21 and the small end of the high pressure turbine 12 are oppositely and non-connected, the large end of the low pressure turbine 21 and the high pressure machine 1 are arranged adjacent, and the small end of the low pressure turbine 21 and the motor 22 are arranged. High-temperature and high-pressure gas discharged from the exhaust end of the high-pressure machine 1 enters the gas inlet end of the low-pressure turbine 21 to push the low-pressure turbine 21 to rotate, so that the motor 22 is driven to generate power, and the exhaust end of the low-pressure turbine 21 is communicated with the flue gas chamber 25.
Preferably, the combustion chamber 13 is a rotary return combustion chamber or an axial flow combustion chamber, the axis of the combustion chamber 13 is coaxial with the installation shafts of the compressor 11 and the high-pressure turbine 12, the combustion chamber 13 is arranged on the side of the high-pressure turbine 12 far away from the compressor 11, or the combustion chamber 13 is arranged between the high-pressure turbine 12 and the compressor 11, and the combustion chamber 13 and high-temperature high-pressure gas generated by mixed combustion of fuel expand in the high-pressure turbine to do work.
Preferably, the regenerator 3 is arranged around the combustion chamber 13, the regenerator 3 is an annular or square box, and the regenerators 3 are arranged integrally or in a split manner, and when in a split manner, the regenerators 3 are arranged uniformly or non-uniformly in one or more.
In this embodiment, the heat exchange air intake mode and the air intake position of the heat regenerator 3 only need to be provided with a multilayer flow heat regenerator 3, the space and the cost are saved due to the multi-stage integral heat exchange, the structure is compact and reasonable, and the heat exchanger is suitable for being applied to the positions with limited space, such as new energy vehicles and cell distributed energy sources.
Preferably, an AC-DC module is connected to the motor 22, and the motor 22 is configured for either passive or active rectification.
Example two
The difference between the present embodiment and the first embodiment is that, as shown in fig. 5, the regenerator 3 in the present embodiment is further provided with a third inlet 35 and a third outlet 36, where the third inlet 35 and the third outlet 36 form a third channel, and the third channel is not communicated with the first channel and the second channel.
In this embodiment, the exhaust end of the high-pressure turbine 12 is further communicated with a third inlet 35 of the regenerator, a third outlet 36 of the regenerator is communicated with the air inlet end of the low-pressure turbine 21, and the exhaust end gas of the high-pressure turbine 12 enters the low-pressure turbine 21 after heat exchange and temperature reduction.
In this embodiment, because the low-pressure turbine 21 has a high conversion rate, the high-temperature gas at the outlet of the combustion chamber 13 can enter the heat regenerator 3 to exchange heat, and then is ejected from the other outlet of the heat regenerator 3 to push the high-pressure turbine 12 to do work by rotating and expanding, so as to improve the heat energy absorption rate, the high-temperature gas pushes the tail gas after the high-pressure turbine 12 does work by rotating and expanding to enter the inlet of the flue gas chamber 25, and further pushes the low-pressure turbine 21 in the flue gas chamber 25 to rotate at a high speed, and the shaft of the low-pressure turbine. Although the high temperature combustion gas enters the regenerator 3 to cause the loss of gas velocity, the residual velocity can still drive the low pressure turbine 21 to work for energy conversion, which improves the overall conversion efficiency of the micro gas turbine.
EXAMPLE III
In the present embodiment, a rotor system for the gas turbine low pressure machine 2 described above is provided.
In the rotor system, the turbine shaft used for installing the low-pressure turbine 21 and the motor shaft used for installing the motor 22 are included, the turbine shaft and the motor shaft are connected through a coupler to jointly form a second rotating shaft 23, a first bearing 241 and a second bearing 242 are arranged between the low-pressure turbine 21 and the coupler, and the motor shaft and the motor body are rotationally connected through a third bearing 243 and a fourth bearing 244.
The low-pressure turbine 21 has a longer wheel base, and the low-pressure turbine 21 passes through the coupling joint with the motor shaft, can keep apart the heat of low-pressure turbine 21 end through this kind of mode, can undertake the great axial thrust of low-pressure turbine 21 end, the setting in low-pressure turbine 21 end flue space of being convenient for simultaneously, compare in connecting low-pressure turbine 21 and motor 22 through an integral shaft, shafting structure have higher stability, this connected mode makes things convenient for the change maintenance of bearing spare part in addition.
In the structure of this embodiment, a first casing and a second casing may be further provided, and the first casing and the second casing are connected by a coupling, wherein the first bearing 241, the second bearing 242, and the low-pressure turbine 21 are disposed in the first casing, and the motor 22, the third bearing 243, and the fourth bearing 244 are disposed in the second casing.
In a specific structure provided in this embodiment, as shown in fig. 6, the rotor system includes a thrust bearing, a first radial bearing, a second radial bearing and a third radial bearing that are sequentially disposed on the second rotating shaft 23, the thrust bearing is disposed between the low-pressure turbine 21 and the coupling and near the low-pressure turbine 21, the first radial bearing is disposed between the low-pressure turbine 21 and the coupling and near the coupling, the second radial bearing is disposed on one side of the motor 22 near the low-pressure turbine 21, and the third radial bearing is disposed on the other side of the motor 22 far from the low-pressure turbine 21.
In another specific structure provided in this embodiment, as shown in fig. 7, the rotor system includes a first radial bearing, a thrust bearing, a second radial bearing and a third radial bearing that are sequentially disposed on the second rotating shaft 23, the first radial bearing is disposed between the low-pressure turbine 21 and the coupler and near the low-pressure turbine 21, the thrust bearing is disposed between the low-pressure turbine 21 and the coupler and near the coupler, the second radial bearing is disposed on one side of the motor 22 near the low-pressure turbine 21, and the third radial bearing is disposed on the other side of the motor 22 far from the low-pressure turbine 21.
Here, the third and fourth bearings may be further provided as thrust bearings, and the corresponding bearing types are provided, which will not be described in detail herein.
Preferably, the thrust bearing and the first radial bearing are non-contact bearings, the second radial bearing and the third radial bearing are non-contact bearings or contact bearings,
further, the thrust bearing adopts a gas-magnetic hybrid thrust bearing or a gas thrust bearing or a magnetic bearing, the first radial bearing adopts a gas-dynamic-static hybrid radial bearing or a gas-magnetic hybrid radial bearing, and the second radial bearing and the third radial bearing can adopt a gas-dynamic-static hybrid radial bearing or a gas-magnetic hybrid radial bearing or a ball bearing.
Because the low-pressure turbine 21 is arranged in the flue gas chamber 25 through the second rotating shaft 23, a non-contact bearing is required to be arranged on the turbine shaft to effectively isolate heat in the flue gas chamber 25, prevent the heat from being conducted to the motor shaft to cause damage to the motor, and improve the reliability and the safety of a power generation system of the gas turbine; the turbine shaft and the motor shaft transmit power respectively and are connected through the coupler, so that the bearing capacity of each shaft can be effectively decomposed while the low-pressure machine 2 is convenient to disassemble, assemble and maintain, and the deformation of the rotating shaft caused by overlong wheel base is prevented.
Preferably, the thrust bearing and the first radial bearing may be provided as an integral bearing having both a radial support function and an axial support function.
As shown in fig. 8 and 9, the integrated bearing 200 includes: a first bearing body 2200, a thrust disc 2300, a second bearing body 2400; the thrust disc 2300 is fixedly connected with the turbine shaft 100 or integrally formed; the first bearing body 2200 and the second bearing body 2400 are sleeved on the turbine shaft 100 and located on two sides of the thrust disc 2300; the first bearing body 2200 has a radial bearing portion 2210 and a thrust bearing portion 2220 which are integrally formed, the radial bearing portion 2210 and the turbine shaft 100 have a predetermined radial gap S1 in the radial direction, and the thrust bearing portion 2220 is mounted opposite to the thrust disk 2300 in the axial direction and has a predetermined first axial gap S2; the second bearing body 2400 is mounted axially opposite the thrust disk 2300 with a predetermined second axial gap S3; the integrated bearing 200 further includes a first bearing housing 2500 and a first bearing end cover 2600, the first bearing housing 2500 is covered on the peripheries of the first bearing body 2200, the thrust disc 2300 and the second bearing body 2400, the first bearing end cover 2600 is mounted on one end of the second bearing body 2400 of the turbine shaft 100, the second bearing body 2400 is fixed in the axial direction, and the first bearing housing 2500 is in transition fit with the first bearing housing 2600.
Specifically, the integrated gas bearing of the present embodiment may be any one of a static pressure gas bearing, a dynamic pressure gas bearing, or a hybrid dynamic and static pressure gas bearing.
When the first bearing body 2200 is provided as a static pressure gas bearing, a first annular air chamber 2230 is provided between the outer periphery of the radial bearing portion 2210 of the first bearing body 2200 and the first bearing housing 2500, and a first through hole 2240 penetrating the first annular air chamber 2230 and the radial gap S1 is provided at the bottom of the first annular air chamber 2230;
a second annular air cavity 2250 is disposed between the thrust bearing portion 2220 of the first bearing body 2200 and the first bearing housing 2500, and a second through hole 2260 penetrating through the second annular air cavity 2250 and the first axial gap S2 is disposed at the bottom of the second annular air cavity 2250;
a third annular air cavity 2270 is arranged between the second bearing body 2400 and the first bearing end cover 2600, and a third through hole 2280 penetrating through the third annular air cavity 2270 and a second axial gap S3 is arranged at the bottom of the third annular air cavity 2270;
meanwhile, the first bearing housing 2500 is also provided with a first air inlet 2510 and a second air inlet 2520 which are used for communicating the first annular air cavity 2230 and the second annular air cavity 2250 with an external air source, and the first bearing end cover 2600 is provided with a third air inlet 2610 which is used for communicating the third annular air cavity 2270 with the external air source.
Preferably, as shown in fig. 9, in this embodiment, the first through hole 2240, the second through hole 2260, and the third through hole 2280 are all set as stepped holes, specifically: the diameter of one side of the stepped hole, which is far away from the gap, is large, the diameter of one side of the stepped hole, which is close to the gap, is small, and the section of the reducing part of the stepped hole can be funnel-shaped or conical. This facilitates machining without affecting the gas pressure in the gap. Because the aperture of the air inlet hole needs to be smaller than a certain value in order to satisfy the air pressure in the gap, the air inlet hole with a small diameter is difficult to process and is easy to block.
Preferably, the first through holes 2240 of the present embodiment is provided in plural number, evenly distributed in the circumferential direction of the radial bearing portion 2210, to form a stable pressure gas film in the circumferential direction of the turbine shaft 100, more smoothly supporting the turbine shaft 100 in the circumferential direction.
Preferably, the first through holes 2240 of the present embodiment is provided in plural number, evenly distributed in the axial direction of the radial bearing portion 2210, to form a stable pressure air film in the axial direction of the turbine shaft 100, more smoothly supporting the turbine shaft 100 in the axial direction.
Preferably, the second through holes 2260 of the present embodiment are provided in plural numbers, and are uniformly distributed on the end surface of the thrust bearing portion 2220 around the axis of the turbine shaft 100, so as to more smoothly support the turbine shaft 100 and the rotor system in the axial direction. As shown in fig. 10. Fig. 10 is a left side view of the first bearing body 2200.
Preferably, the third through holes 2280 of the present embodiment are provided in plural numbers, and are uniformly distributed on the end surface of the second bearing body 2400 with the axis of the turbine shaft 100 as the center, so as to support the turbine shaft 100 and the rotor system more smoothly in the axial direction.
When the integrated gas bearing of the present embodiment is provided as a dynamic pressure bearing, a dynamic pressure generating groove is provided on an inner diameter surface of the radial bearing portion 2210 of the first bearing body 2200 or a portion of the turbine shaft 100 where the radial bearing portion 2210 is mounted; a dynamic pressure generating groove is provided in an end surface of the thrust bearing portion 2220 of the first bearing body 2200 facing the thrust disk 2300 or an end surface of the thrust disk surface 2300 facing the thrust bearing portion 2220; a dynamic pressure generating groove is provided on an end surface of the second bearing body 2400 facing the thrust disk 2300 or an end surface of the thrust disk 2300 facing the second bearing body 2400.
When the integrated gas bearing of the present embodiment is provided as a hybrid bearing of dynamic and static pressures, it has both the features of the hydrostatic bearing and the dynamic pressure bearing.
In the integrated gas bearing, the first bearing body 2200 has both the radial bearing portion 2210 and the thrust bearing portion 2220, and therefore, it is sufficient to ensure the perpendicularity between the axial direction and the action surface of the thrust bearing portion 2220 by machining the thrust bearing portion 2220 with the axial direction as a reference, or the perpendicularity between the action surface of the thrust bearing portion 2220 and the axial direction by machining the inner diameter of the radial bearing portion 2210 with the action surface of the thrust bearing portion 2220 as a reference in the machining process. The processing technology is simple and easy to operate, the processing precision is high, meanwhile, the precision of combined assembly is not required to be considered in the assembly process, and the assembly technology is simple.
In another specific structure provided in this embodiment, as shown in fig. 11, a first radial bearing, a second radial bearing, a third radial bearing and a fourth radial bearing are sequentially disposed on the second rotating shaft 23, the first radial bearing is disposed between the low-pressure turbine 21 and the coupler and near the low-pressure turbine 21, the second radial bearing is disposed between the low-pressure turbine 21 and the coupler and near the coupler, the third radial bearing is disposed on one side of the motor 22 near the low-pressure turbine 21, and the fourth radial bearing is disposed on the other side of the motor 22 far from the low-pressure turbine 21.
Preferably, the first and second radial bearings are contact bearings, the third and fourth radial bearings are non-contact bearings or contact bearings,
furthermore, the first radial bearing and the second radial bearing adopt ball bearings, the third radial bearing and the fourth radial bearing adopt a gas dynamic and static pressure mixed radial bearing or a gas magnetic mixed radial bearing or a ball bearing, the first radial bearing and the second radial bearing adopt the ball bearings to offset axial force and simultaneously play roles of the radial bearing and a thrust bearing,
here, the third and fourth bearings may be further provided as thrust bearings, and the corresponding bearing types are provided, which will not be described in detail herein.
Example four
In the present embodiment, another rotor system for the gas turbine low pressure machine 2 described above is provided.
This rotor system level sets up, and second pivot 23 formula pivot as an organic whole is provided with low-pressure turbine 21 and motor 22 on the second pivot 23, is provided with first bearing 241, second bearing 242 between low-pressure turbine 21 and the motor 22, and motor 22 keeps away from low-pressure turbine 21 one side and is provided with third bearing 243.
In a specific structure provided in this embodiment, as shown in fig. 12, the rotor system includes a thrust bearing, a first radial bearing, and a second radial bearing, which are sequentially disposed on the second rotating shaft 23.
In another specific structure provided in this embodiment, referring to fig. 13, the rotor system includes a first radial bearing, a thrust bearing, and a second radial bearing sequentially disposed on the second rotating shaft 23.
Preferably, the thrust bearing and the first radial bearing are non-contact bearings, and the second radial bearing is a non-contact bearing or a contact bearing.
Further, the thrust bearing adopts a gas-magnetic hybrid thrust bearing or a gas thrust bearing or a magnetic bearing, the first radial bearing adopts a gas-dynamic-static hybrid radial bearing or a gas-magnetic hybrid radial bearing, and the second radial bearing can adopt a gas-dynamic-static hybrid radial bearing or a gas-magnetic hybrid radial bearing or a ball bearing.
In another specific structure provided in this embodiment, referring to fig. 14, the rotor system includes a first radial bearing, a second radial bearing, and a third radial bearing sequentially disposed on the second rotating shaft 23.
Preferably, the first radial bearing, the second radial bearing are contact bearings, the third radial bearing is a non-contact bearing or a contact bearing,
furthermore, the first radial bearing and the second radial bearing adopt ball bearings, the third radial bearing adopts a gas dynamic and static pressure mixed radial bearing or a gas magnetic mixed radial bearing or a ball bearing, the first radial bearing and the second radial bearing adopt the ball bearings to offset the axial force, and the radial bearing and the thrust bearing are simultaneously used.
In the rotor system of the embodiment, the low-pressure turbine 21 has a low shaft rotation speed, and the radial load and the axial thrust of the rotating shaft are greatly reduced compared with those of a conventional integrated high-speed micro gas turbine, and the requirement on the strength of the rotating shaft is also reduced, so that the integrated rotating shaft can be used for connecting the low-pressure turbine 21 and the motor 22, the number of parts is reduced, and the design reliability is improved.
The micro gas turbine has a simple and compact structure, saves the installation space, is convenient to install and carry quickly, and can well meet the small-scale and distributed requirements of distributed power supply; the moving parts are few, the structure is simple and compact, and therefore the reliability is good, and the manufacturing cost and the maintenance cost are low; good environmental adaptability and high power supply quality.
The operation reliability of the whole system is as high as 99.996%, and the average annual shutdown maintenance time is not more than 2 hours. The single machine power of the micro gas turbine is 10-100 KW, the micro gas turbine can run at step power and step rotating speed, and the highest rotating speed reaches 140000 RPM; the fuel consumption is less.
Preferably, the rotating speed of the 15KW micro-combustion engine with the heat regenerator is 0-140000 RPM, and when the fuel is kerosene, the oil consumption is 50-600 g/kWh; when the fuel is natural gas, the consumption of the natural gas is 0.15m3/kWh～0.5m3/kWh. The rotating speed of a 15KW micro-combustion engine without a heat regenerator is 0-140000 RPM, and when the fuel is kerosene, the oil consumption is 400-1000 g/kWh; when the fuel is natural gas, the consumption of the natural gas is 0.4m3/kWh～1m3/kWh。
Preferably, the rotating speed of a 45KW micro-combustion engine with a heat regenerator is 0-80000 RPM, and when the fuel is kerosene, the oil consumption is 200-500 g/kWh; when the fuel is natural gas, the consumption of the natural gas is 0.2m3/kWh～0.5m3/kWh. The rotating speed of a 45KW micro-combustion engine without a heat regenerator is 0-80000 RPM, and when the fuel is kerosene, the oil consumption is 400-900 g/kWh; when the fuel is natural gas, the consumption of the natural gas is 0.5m3/kWh～1m3/kWh。
The above description is only a preferred embodiment of the application and is illustrative of the principles of the technology employed. It will be appreciated by a person skilled in the art that the scope of the invention as referred to in the present application is not limited to the embodiments with a specific combination of the above-mentioned features, but also covers other embodiments with any combination of the above-mentioned features or their equivalents without departing from the inventive concept. For example, the features described above have similar functions to (but are not limited to) those disclosed in this application.
Claims (23)
1. A micro gas turbine, comprising:
a high pressure machine, a low pressure machine and a heat regenerator;
the high-pressure machine comprises a gas compressor, a high-pressure turbine, a combustion chamber and a high-pressure rotor system, wherein the gas compressor and the high-pressure turbine are coaxially and fixedly arranged on the high-pressure rotor system back to back;
the low-pressure machine comprises a low-pressure turbine, a motor, a low-pressure rotor system and a flue gas chamber; the low-pressure turbine and the motor are sequentially coaxially and fixedly arranged on the low-pressure rotor system;
the gas inlet end of the gas compressor is communicated with the outside, the gas outlet end of the gas compressor is communicated with the first inlet of the heat regenerator, the first outlet of the heat regenerator is communicated with the inlet of the combustion chamber, the gas outlet end of the combustion chamber is communicated with the gas inlet end of the high-pressure turbine, the gas outlet end of the high-pressure turbine is communicated with the gas inlet end of the low-pressure turbine, the gas outlet end of the low-pressure turbine is communicated with the inlet of the gas chamber, the outlet of the gas chamber is communicated with the second inlet of the heat regenerator, and the second outlet of the heat regenerator is.
2. The micro gas turbine according to claim 1, wherein the compressor is a centrifugal compressor, and a starter motor is provided at a front end of the compressor.
3. The micro gas turbine according to claim 1, wherein the low pressure turbine is a centrifugal or centripetal or axial turbine;
when the low-pressure turbine is a centrifugal turbine, the small end of the low-pressure turbine and the small end of the high-pressure turbine are oppositely and non-connected;
when the low-pressure turbine is a centripetal turbine, the large end of the low-pressure turbine and the small end of the high-pressure turbine are arranged oppositely and in the same direction in a non-connected mode.
4. The micro gas turbine according to claim 1, wherein the combustor is a rotary reverse flow combustor or an axial flow combustor, and the axis of the combustor is coaxial with the installation axes of the compressor and the high pressure turbine;
the combustion chamber is arranged on one side of the high-pressure turbine far away from the compressor, or the combustion chamber is arranged between the high-pressure turbine and the compressor.
5. The micro gas turbine according to claim 1, wherein the regenerator is disposed circumferentially outside the combustion chamber;
the heat regenerator is an annular or square box body;
the heat regenerators are arranged in an integrated or split mode, and when the heat regenerators are arranged in a split mode, the heat regenerators are uniformly or non-uniformly arranged;
the first inlet and the second outlet of the heat regenerator are cold ends, and the first inlet and the second inlet are hot ends, wherein the first inlet and the first outlet form a first channel, the second inlet and the second outlet form a second channel, and the first channel and the second channel are not communicated.
6. The micro gas turbine according to claim 1, wherein the regenerator is further provided with a third inlet, a third outlet;
the exhaust end of the high-pressure turbine is also communicated with a third inlet of the heat regenerator, and a third outlet of the heat regenerator is communicated with the air inlet end of the low-pressure turbine.
7. The micro gas turbine according to claim 6, wherein the regenerator is disposed circumferentially outside the combustion chamber;
the heat regenerator is an annular or square box body;
the heat regenerators are arranged in an integrated or split mode, and when the heat regenerators are arranged in a split mode, the heat regenerators are uniformly or non-uniformly arranged;
the first inlet, the second outlet and the third outlet of the regenerator are cold ends, and the first outlet, the second inlet and the third inlet are hot ends, wherein the first inlet and the first outlet form a first channel, the second inlet and the second outlet form a second channel, the third inlet and the third outlet form a third channel, and the first channel, the second channel and the third channel are not communicated.
8. The micro gas turbine according to any one of claims 1 to 7, wherein the low pressure rotor system comprises a turbine shaft for mounting the low pressure turbine, a motor shaft for mounting the motor, the turbine shaft and the motor shaft being coupled by a coupling;
a first bearing and a second bearing are arranged between the low-pressure turbine and the coupler, and a motor shaft is rotatably connected with the motor body through a third bearing and a fourth bearing.
9. The micro gas turbine according to claim 8, wherein the low pressure spool system further comprises a first casing and a second casing, the first casing coupled to the second casing by a coupling, wherein the first bearing, the second bearing, the low pressure turbine are disposed in the first casing, and the electric machine, the third bearing, and the fourth bearing are disposed in the second casing.
10. The micro gas turbine according to claim 8, wherein the first bearing, the second bearing, the third bearing and the fourth bearing are a thrust bearing, a first radial bearing, a second radial bearing and a third radial bearing, respectively, the thrust bearing is disposed between the low-pressure turbine and the coupling and near the low-pressure turbine, the first radial bearing is disposed between the low-pressure turbine and the coupling and near the coupling, the second radial bearing is disposed on one side of the electric machine near the low-pressure turbine, and the third radial bearing is disposed on the other side of the electric machine far from the low-pressure turbine;
or the first bearing, the second bearing, the third bearing and the fourth bearing are respectively a first radial bearing, a thrust bearing, a second radial bearing and a third radial bearing;
the first radial bearing is arranged at a position between the low-pressure turbine and the coupler and close to the low-pressure turbine, the thrust bearing is arranged at a position between the low-pressure turbine and the coupler and close to the coupler, the second radial bearing is arranged at one side of the motor close to the low-pressure turbine, and the third radial bearing is arranged at the other side of the motor far away from the low-pressure turbine.
11. The micro gas turbine according to claim 10, wherein the thrust bearing and the first radial bearing are non-contact bearings, and the second radial bearing and the third radial bearing are non-contact bearings or contact bearings.
12. The micro gas turbine according to claim 11, wherein the thrust bearing is a gas-magnetic hybrid thrust bearing or an air thrust bearing or a magnetic bearing; the first radial bearing adopts a gas dynamic and static pressure mixed radial bearing or a gas magnetic mixed radial bearing, and the second radial bearing and the third radial bearing both adopt a gas dynamic and static pressure mixed radial bearing or a gas magnetic mixed radial bearing or a ball bearing.
13. The micro gas turbine according to claim 12, wherein the thrust bearing, the first radial bearing are provided as an integral bearing;
the integrated bearing includes:
the thrust disc is fixedly connected with the turbine shaft or integrally formed;
the first bearing body and the second bearing body are sleeved on the turbine shaft and positioned on two sides of the thrust disc;
wherein the first bearing body has a radial bearing portion and a thrust bearing portion which are integrally formed, the radial bearing portion having a predetermined radial clearance in a radial direction from the turbine shaft so as to form the first radial bearing;
the thrust bearing portion is mounted axially opposite the thrust disk with a predetermined first axial gap, and the second bearing body is mounted axially opposite the thrust disk with a predetermined second axial gap, thereby forming the thrust bearing.
14. The micro gas turbine according to claim 8, wherein the first bearing, the second bearing, the third bearing and the fourth bearing are a first radial bearing, a second radial bearing, a third radial bearing and a fourth radial bearing, respectively, the first radial bearing is disposed between the low pressure turbine and the coupling and near the low pressure turbine, the second radial bearing is disposed between the low pressure turbine and the coupling and near the coupling, the third radial bearing is disposed on one side of the motor near the low pressure turbine, and the fourth radial bearing is disposed on the other side of the motor far from the low pressure turbine.
15. The micro gas turbine according to claim 14, wherein the first radial bearing and the second radial bearing are both contact bearings, and the third radial bearing and the fourth radial bearing are non-contact bearings or contact bearings.
16. The micro gas turbine according to claim 15, wherein the first radial bearing, the second radial bearing are ball bearings, and the third radial bearing and the fourth radial bearing are hybrid gas-hybrid radial bearings or hybrid gas-magnetic radial bearings or ball bearings.
17. The micro gas turbine according to any one of claims 1 to 7, wherein the low pressure rotor system comprises a low pressure rotating shaft, the low pressure rotating shaft is an integrated rotating shaft, the low pressure turbine and the motor are mounted on the low pressure rotating shaft, a first bearing and a second bearing are arranged between the low pressure turbine and the motor, and a third bearing is arranged on one side of the motor, which is far away from the low pressure turbine.
18. The micro gas turbine of claim 17, wherein the first, second, and third bearings are thrust bearings, first radial bearings, and second radial bearings, respectively;
or, the first bearing, the second bearing and the third bearing are respectively a first radial bearing, a thrust bearing and a second radial bearing.
19. The micro gas turbine according to claim 18, wherein the thrust bearing and the first radial bearing are both non-contact bearings, and the second radial bearing is either a non-contact bearing or a contact bearing.
20. The micro gas turbine according to claim 19, wherein the thrust bearing is a gas-magnetic hybrid thrust bearing or an air thrust bearing or a magnetic bearing, the first radial bearing is a gas-hybrid hydrodynamic radial bearing or a gas-magnetic hybrid radial bearing, and the second radial bearing is a gas-hybrid hydrodynamic radial bearing or a gas-magnetic hybrid radial bearing or a ball bearing.
21. The micro gas turbine of claim 17, wherein the first bearing, the second bearing, and the third bearing are a first radial bearing, a second radial bearing, and a third radial bearing, respectively.
22. The micro gas turbine according to claim 21, wherein the first radial bearing, the second radial bearing are both contact bearings, and the third radial bearing is a non-contact bearing or a contact bearing.
23. The micro gas turbine according to claim 22, wherein the first radial bearing, the second radial bearing and the third radial bearing are ball bearings and hybrid gas-hybrid radial bearings or hybrid gas-magnetic radial bearings or ball bearings.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911370913.1A CN111058945A (en) | 2019-12-27 | 2019-12-27 | Miniature gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911370913.1A CN111058945A (en) | 2019-12-27 | 2019-12-27 | Miniature gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111058945A true CN111058945A (en) | 2020-04-24 |
Family
ID=70304037
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911370913.1A Pending CN111058945A (en) | 2019-12-27 | 2019-12-27 | Miniature gas turbine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111058945A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112727601A (en) * | 2020-12-24 | 2021-04-30 | 北航（四川）西部国际创新港科技有限公司 | Micro gas turbine and thermal power generation system |
| WO2022105214A1 (en) * | 2020-11-18 | 2022-05-27 | 至玥腾风科技集团有限公司 | Dual-shaft power generation gas turbine |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030059295A1 (en) * | 2001-09-26 | 2003-03-27 | Olsen Andrew J. | Interchangeable power turbine cartridge assembly |
| US20040103666A1 (en) * | 2001-04-06 | 2004-06-03 | Volvo Aero Corporation | Method and arrangement for proving a gas turbine, and engine-braking therefore |
| JP2006183608A (en) * | 2004-12-28 | 2006-07-13 | Kawasaki Heavy Ind Ltd | Excessive speed avoidance device of regenerative type gas turbine |
| CN105604698A (en) * | 2015-12-29 | 2016-05-25 | 中国航空工业集团公司沈阳发动机设计研究所 | Micro gas turbine |
| CN107288758A (en) * | 2016-03-30 | 2017-10-24 | 中国科学院工程热物理研究所 | The combination gas jet power unit and conversion method of a kind of split axle |
| CN211343126U (en) * | 2019-12-27 | 2020-08-25 | 迅玲腾风汽车动力科技(北京)有限公司 | Miniature gas turbine |
-
2019
- 2019-12-27 CN CN201911370913.1A patent/CN111058945A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20040103666A1 (en) * | 2001-04-06 | 2004-06-03 | Volvo Aero Corporation | Method and arrangement for proving a gas turbine, and engine-braking therefore |
| US20030059295A1 (en) * | 2001-09-26 | 2003-03-27 | Olsen Andrew J. | Interchangeable power turbine cartridge assembly |
| JP2006183608A (en) * | 2004-12-28 | 2006-07-13 | Kawasaki Heavy Ind Ltd | Excessive speed avoidance device of regenerative type gas turbine |
| CN105604698A (en) * | 2015-12-29 | 2016-05-25 | 中国航空工业集团公司沈阳发动机设计研究所 | Micro gas turbine |
| CN107288758A (en) * | 2016-03-30 | 2017-10-24 | 中国科学院工程热物理研究所 | The combination gas jet power unit and conversion method of a kind of split axle |
| CN211343126U (en) * | 2019-12-27 | 2020-08-25 | 迅玲腾风汽车动力科技(北京)有限公司 | Miniature gas turbine |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2022105214A1 (en) * | 2020-11-18 | 2022-05-27 | 至玥腾风科技集团有限公司 | Dual-shaft power generation gas turbine |
| CN112727601A (en) * | 2020-12-24 | 2021-04-30 | 北航（四川）西部国际创新港科技有限公司 | Micro gas turbine and thermal power generation system |
| CN112727601B (en) * | 2020-12-24 | 2022-04-05 | 北航（四川）西部国际创新港科技有限公司 | Micro gas turbine and thermal power generation system |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US6430917B1 (en) | Single rotor turbine engine | |
| US6897578B1 (en) | Integrated microturbine gearbox generator assembly | |
| US20120306206A1 (en) | Ultra high pressure turbomachine for waste heat recovery | |
| US10982713B2 (en) | Closed cycle heat engine | |
| WO2021129431A1 (en) | Combined cooling, heating and power micro gas turbine device | |
| CN211343126U (en) | Miniature gas turbine | |
| CN111058945A (en) | Miniature gas turbine | |
| WO2022127054A1 (en) | Micro gas turbine having axial force balancing structure | |
| CN111042921A (en) | Multistage turbine type micro gas turbine | |
| CN211474268U (en) | Rotor system and micro gas turbine generator set | |
| CN110725748B (en) | Micro turbine electric hybrid distributed power device | |
| JP4746499B2 (en) | Atmospheric pressure combustion turbine system with improved shaft cooling structure | |
| CN211343135U (en) | Multistage turbine type micro gas turbine | |
| CN111042923A (en) | Rotor system and micro gas turbine generator set | |
| US11867119B2 (en) | Electric generator and multi-shaft gas turbine engine for aircraft equipped with electric generator | |
| CN211598832U (en) | Micro turbine electricity hybrid distributed power device | |
| CN211598834U (en) | Rotor system and micro gas turbine generator set | |
| CN211474265U (en) | Rotor system and micro gas turbine generator set | |
| CN113623071A (en) | Magnetic suspension outer rotor starting integrated motor for gas turbine | |
| CN110985206A (en) | Rotor system and micro gas turbine generator set | |
| CN111042925A (en) | Rotor system and micro gas turbine generator set | |
| KR20220156619A (en) | Integral hermetically sealed turboexpander-generator with overhanging turbomachinery | |
| JP4987427B2 (en) | Atmospheric pressure combustion turbine system with cooling structure for working gas inlet | |
| CN211598835U (en) | Rotor system and micro gas turbine generator set | |
| US20230318404A1 (en) | Rotary electric machine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| TA01 | Transfer of patent application right | ||
| TA01 | Transfer of patent application right |
Effective date of registration: 20210108 Address after: 100029 room 104, No.101, building 3, yard a 29, North Third Ring Middle Road, Xicheng District, Beijing Applicant after: Zhiyue Tengfeng Technology Group Co.,Ltd. Applicant after: XUNLING TENGFENG AUTOMOTIVE POWER TECHNOLOGY (BEIJING) Co.,Ltd. Address before: 100176 room 1202a, 12 / F, block B, building 1, yard 19, Ronghua Middle Road, economic and Technological Development Zone, Daxing District, Beijing Applicant before: XUNLING TENGFENG AUTOMOTIVE POWER TECHNOLOGY (BEIJING) Co.,Ltd. |
|
| CB02 | Change of applicant information | ||
| CB02 | Change of applicant information |
Address after: 100029 room 104, No.101, building 3, yard a 29, North Third Ring Middle Road, Xicheng District, Beijing Applicant after: Zhiyue Tengfeng Technology Group Co.,Ltd. Applicant after: Yongxu Tengfeng new energy power technology (Beijing) Co.,Ltd. Address before: 100029 room 104, No.101, building 3, yard a 29, North Third Ring Middle Road, Xicheng District, Beijing Applicant before: Zhiyue Tengfeng Technology Group Co.,Ltd. Applicant before: XUNLING TENGFENG AUTOMOTIVE POWER TECHNOLOGY (BEIJING) Co.,Ltd. |
|
| TA01 | Transfer of patent application right | ||
| TA01 | Transfer of patent application right |
Effective date of registration: 20230403 Address after: Room 104, Room 101, Building 3, Yard A29, North Third Ring Middle Road, Xicheng District, Beijing, 100011 Applicant after: Zhiyue Tengfeng Technology Group Co.,Ltd. Applicant after: Beijing Yongxu Tengfeng New Energy Power Technology Development Co.,Ltd. Address before: 100029 room 104, No.101, building 3, yard a 29, North Third Ring Middle Road, Xicheng District, Beijing Applicant before: Zhiyue Tengfeng Technology Group Co.,Ltd. Applicant before: Yongxu Tengfeng new energy power technology (Beijing) Co.,Ltd. |