CN103982302B - For cooling mechanism and the Gas Turbine Generating Units of Gas Turbine Generating Units - Google Patents
For cooling mechanism and the Gas Turbine Generating Units of Gas Turbine Generating Units Download PDFInfo
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- CN103982302B CN103982302B CN201410221711.1A CN201410221711A CN103982302B CN 103982302 B CN103982302 B CN 103982302B CN 201410221711 A CN201410221711 A CN 201410221711A CN 103982302 B CN103982302 B CN 103982302B
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- 238000001816 cooling Methods 0.000 title claims abstract description 35
- 238000009423 ventilation Methods 0.000 claims abstract description 6
- 238000002347 injection Methods 0.000 claims description 23
- 239000007924 injection Substances 0.000 claims description 23
- 230000008676 import Effects 0.000 claims description 6
- 230000036316 preload Effects 0.000 claims description 4
- 125000006850 spacer group Chemical group 0.000 claims description 4
- 230000005540 biological transmission Effects 0.000 claims description 3
- 239000010687 lubricating oil Substances 0.000 claims description 3
- 230000000694 effects Effects 0.000 abstract description 6
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- 238000000034 method Methods 0.000 description 6
- 229910000838 Al alloy Inorganic materials 0.000 description 5
- 230000008859 change Effects 0.000 description 5
- 229910001069 Ti alloy Inorganic materials 0.000 description 3
- 230000008901 benefit Effects 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 238000012423 maintenance Methods 0.000 description 3
- 230000001105 regulatory effect Effects 0.000 description 3
- 238000012546 transfer Methods 0.000 description 3
- 238000005452 bending Methods 0.000 description 2
- 238000002485 combustion reaction Methods 0.000 description 2
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 150000002148 esters Chemical class 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 238000005057 refrigeration Methods 0.000 description 2
- NDKWCCLKSWNDBG-UHFFFAOYSA-N zinc;dioxido(dioxo)chromium Chemical compound [Zn+2].[O-][Cr]([O-])(=O)=O NDKWCCLKSWNDBG-UHFFFAOYSA-N 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000000567 combustion gas Substances 0.000 description 1
- 238000009792 diffusion process Methods 0.000 description 1
- 230000017525 heat dissipation Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000003921 oil Substances 0.000 description 1
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- 239000003507 refrigerant Substances 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
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Abstract
The invention discloses a kind of cooling mechanism for Gas Turbine Generating Units and Gas Turbine Generating Units, for the cooling mechanism of Gas Turbine Generating Units, comprise for forced ventilation in Gas Turbine Generating Units with take away heat axial flow compressor structure and in order to transmitting torque and live axle flow air compressor structure running driving mechanism, driving mechanism is connected with the output terminal of gas turbine drive case and links with the output terminal of gas turbine drive case; Axial flow compressor structure and/or driving mechanism offer air intake passage; The air-supply end of axial flow compressor structure leads to Gas Turbine Generating Units inside.The present invention initiates the active heat removal mode using convection current cooling, for unit provides cooled gas endlessly, takes away heat unnecessary in unit, thus serves vital effect to balancing machine indoor environment.
Description
Technical field
The present invention relates to Gas Turbine Generating Units technical field, especially, relate to a kind of cooling mechanism for Gas Turbine Generating Units.In addition, the invention still further relates to a kind of Gas Turbine Generating Units comprising above-mentioned cooling mechanism.
Background technique
The automatic power supply that gas turbo-generator set is equipped usually used as various vehicular weapons.When Gas Turbine Generating Units be in the changed power amplitude of the state of working long hours or Gas Turbine Generating Units large, frequent high time, in cabin, heat load is more and more higher, the passive radiating effect of generator worse and worse, thus affect the normal work of whole generator set, in some environments, even overheated burning can be caused.
At present, domestic Gas Turbine Generating Units is all with passive heat radiation for main heat sink mode, and this kind of radiating mode speed is slow, and radiating effect is also not obvious, and in unit running process, in cabin, temperature can be more and more higher, thus affects the operation of whole unit.
Summary of the invention
The object of the invention is to provide a kind of cooling mechanism for Gas Turbine Generating Units and Gas Turbine Generating Units, is a kind of active heat removal mode.The present invention initiates the active heat removal mode using convection current cooling, for unit provides cooled gas endlessly, takes away heat unnecessary in unit, thus serves vital effect to balancing machine indoor environment.Engine room ventilation is forced by this device, take away the heat that combustion engine and generator produce in the course of the work, ensure the normal work of each element in unit, slow with the passive radiating mode heat dissipation rate solving existing Gas Turbine Generating Units, radiating effect is not obvious, cause temperature in cabin constantly to raise, have influence on the technical problem of the operation of whole unit etc.
For achieving the above object, the technical solution used in the present invention is as follows:
A kind of cooling mechanism for Gas Turbine Generating Units, comprise for forced ventilation in Gas Turbine Generating Units with take away heat axial flow compressor structure and in order to transmitting torque and live axle flow air compressor structure running driving mechanism, driving mechanism is connected with the output terminal of gas turbine drive case and links with the output terminal of gas turbine drive case; Axial flow compressor structure and/or driving mechanism offer air intake passage.
Further, driving mechanism comprises the rotor assembly in order to driving torque, the stator assembly in order to support rotor assembly and is located at rotor assembly and the outer field inlet casing of stator assembly, stator assembly is fixed in inlet casing, and stator assembly is sheathed on outside rotor assembly.
Further, rotor assembly comprises in order to the impeller shaft of transmitting torque, in order to transmit the blower fan gear of gas turbine drive case output torque and the locking nut in order to fixing blower fan gear to impeller shaft; Locking nut is by blower fan wheel gear locking on impeller shaft, and the retarder end gear of blower fan gear and gas turbine drive case engages each other.
Further, stator assembly comprise for by the axial force transmission of rotor assembly to the neck bush of inlet casing, in order to intercept the injection loop of lubricating oil and two in order to support the ball bearing of impeller shaft; Adopt interference fit to be connected between neck bush with inlet casing, injection loop to be arranged between two ball bearings and to adopt Spielpassung to be connected with neck bush, and ball bearing, neck bush and injection loop surround a shared bearing bore.
Further, ball bearing comprises the first ball bearing and the second ball bearing; First ball bearing imports end layout near the moment of torsion of impeller shaft, first end face of the outer shroud of the first ball bearing and the first end face of injection loop are close to layout, and the second end face of the outer shroud of the first ball bearing is by spacer, circlip and neck bush end face stationary positioned; Second ball bearing is arranged near the torque output of impeller shaft, and the outer shroud of the second ball bearing is connected with the second end face of injection loop by Compress Spring, and Compress Spring forms the preload of opposing rotor assembly axial force; The relative distance between the inner ring of the first ball bearing and the inner ring of the second ball bearing is limited by distance ring between the inner ring of the first ball bearing and the inner ring of the second ball bearing, the end face inner ring of the first ball bearing being imported end side by impeller shaft moment of torsion into is compressed by blower fan gear and locking nut, and the inner ring of the second ball bearing is close to layout by the end face of impeller shaft torque output side and disc.
Further, axial flow compressor structure comprise be located on air intake passage exhaust outlet in order to by the air entered guiding Gas Turbine Generating Units direction inlet guiding, in order to the air pressure that inlet guiding is imported contract lead Gas Turbine Generating Units direction impeller and be located at inlet guiding and the outer field axial flow casing of impeller; Inlet guiding is fixed in axial flow casing by axial flow outer shroud, and impeller is arranged on the torque output of impeller shaft and rotates with impeller shaft.
Further, seam is adopted to locate and be connected and fixed by link between inlet casing and axial flow casing.
Further, on the impeller shaft at position that is connected with Gas Turbine Generating Units of axial flow compressor structure, the pressurized air be also provided with for being imported by impeller carries out expansion supercharging and imports the exhaust section assembly in Gas Turbine Generating Units.
Further, the intake grill of air intake passage is provided with the spiral case increasing intake grill wind flow.
According to a further aspect in the invention, additionally provide a kind of Gas Turbine Generating Units, it comprises the above-mentioned cooling mechanism for Gas Turbine Generating Units.
The present invention has following beneficial effect:
Cooling mechanism structure of the present invention is simple, volume is little, lightweight, reliability is high, and technology capability is good with assembling maintenance; Have employed the active heat removal mode of a kind of high efficiency forced convection cooling, driving mechanism is connected with the output terminal of gas turbine drive case and links with the output terminal of gas turbine drive case, rotation speed of fan can be regulated according to the changed power of generator set, thus change cooling air quantity, make the indoor environment of generator set relatively stable, ensure that each element of generator set normally works, ensure the normal operation of Gas Turbine Generating Units in power adjustment procedure.
Except object described above, feature and advantage, the present invention also has other object, feature and advantage.Below with reference to figure, the present invention is further detailed explanation.
Accompanying drawing explanation
The accompanying drawing forming a application's part is used to provide a further understanding of the present invention, and schematic description and description of the present invention, for explaining the present invention, does not form inappropriate limitation of the present invention.In the accompanying drawings:
Fig. 1 is the structural representation of the cooling mechanism for Gas Turbine Generating Units of the preferred embodiment of the present invention;
Fig. 2 is the structural representation of the Gas Turbine Generating Units of the preferred embodiment of the present invention;
Fig. 3 is the structural representation of the inlet guiding of the preferred embodiment of the present invention;
Fig. 4 is the structural representation of the exhaust section assembly of the preferred embodiment of the present invention;
Fig. 5 is the structural representation of the rotor assembly of the preferred embodiment of the present invention.
Marginal data:
1, axial flow compressor structure; 101, inlet guiding; 102, impeller; 103, axial flow casing; 2, driving mechanism; 201, rotor assembly; 2011, impeller shaft; 2012, blower fan gear; 2013, locking nut; 202, stator assembly; 2021, neck bush; 2022, injection loop; 2023, ball bearing; 2023a, the first ball bearing; 2023b, the second ball bearing; 203, inlet casing; 3, air intake passage; 4, distance ring; 5, disc; 6, axial flow outer shroud; 7, Gas Turbine Generating Units; 8, exhaust section assembly; 9, Compress Spring; 10, spiral case.
Embodiment
Below in conjunction with accompanying drawing, embodiments of the invention are described in detail, but the present invention can by the multitude of different ways that limits and cover implement.
Fig. 1 is the structural representation of the cooling mechanism for Gas Turbine Generating Units of the preferred embodiment of the present invention; Fig. 2 is the structural representation of the Gas Turbine Generating Units of the preferred embodiment of the present invention; Fig. 3 is the structural representation of the inlet guiding of the preferred embodiment of the present invention; Fig. 4 is the structural representation of the exhaust section assembly of the preferred embodiment of the present invention; Fig. 5 is the structural representation of the rotor assembly of the preferred embodiment of the present invention.
As shown in Figure 1, the cooling mechanism for Gas Turbine Generating Units of the present embodiment, comprise for forced ventilation in Gas Turbine Generating Units 7 with take away heat axial flow compressor structure 1 and in order to transmitting torque and live axle flow air compressor structure 1 running driving mechanism 2, driving mechanism 2 is connected with the output terminal of gas turbine drive case and links with the output terminal of gas turbine drive case; Axial flow compressor structure 1 and/or driving mechanism 2 offer air intake passage 3.The air-supply end of axial flow compressor structure 1 leads to Gas Turbine Generating Units 7 inside.Cooling mechanism structure of the present invention is simple, volume is little, lightweight, reliability is high, and technology capability is good with assembling maintenance; Have employed the active heat removal mode of a kind of high efficiency forced convection cooling, driving mechanism 2 is connected with the output terminal of gas turbine drive case and links with the output terminal of gas turbine drive case, rotation speed of fan can be regulated according to the changed power of generator set, thus change cooling air quantity, make the indoor environment of generator set relatively stable, ensure that each element of generator set normally works, ensure the normal operation of Gas Turbine Generating Units in power adjustment procedure.
As shown in Figure 1, Figure 2 with shown in Fig. 5, in the present embodiment, driving mechanism 2 comprises the rotor assembly 201 in order to driving torque, the stator assembly 202 in order to support rotor assembly 201 and is located at rotor assembly 201 and the outer field inlet casing 203 of stator assembly 202, stator assembly 202 is fixed in inlet casing 203, and stator assembly 202 is sheathed on outside rotor assembly 201.
As shown in Figure 1, Figure 2 with shown in Fig. 5, in the present embodiment, rotor assembly 201 comprises in order to the impeller shaft 2011 of transmitting torque, in order to transmit the blower fan gear 2012 of gas turbine drive case output torque and the locking nut 2013 in order to fixing blower fan gear 2012 to impeller shaft 2011.Blower fan gear 2012 is locked on impeller shaft 2011 by locking nut 2013.Blower fan gear 2012 engages each other with the retarder end gear of gas turbine drive case.
As shown in Figure 1, Figure 2 with shown in Fig. 5, in the present embodiment, stator assembly 202 comprise for by the axial force transmission of rotor assembly 201 to the neck bush 2021 of inlet casing 203, in order to intercept the injection loop 2022 of lubricating oil and two in order to support the ball bearing 2023 of impeller shaft 2011.Interference fit is adopted to be connected between neck bush 2021 with inlet casing 203.Injection loop 2022 to be arranged between two ball bearings 2023 and to adopt Spielpassung to be connected with neck bush 2021, and ball bearing 2023, neck bush 2021 and injection loop 2022 surround a shared bearing bore.
As shown in Figure 1, Figure 2 with shown in Fig. 5, in the present embodiment, ball bearing 2023 comprises the first ball bearing 2023a and the second ball bearing 2023b.First ball bearing 2023a imports end layout near the moment of torsion of impeller shaft 2011.First end face of the outer shroud of the first ball bearing 2023a and the first end face of injection loop 2022 are close to layout.Second end face of the outer shroud of the first ball bearing 2023a is by spacer, circlip and neck bush 2021 end face stationary positioned.Second ball bearing 2023b arranges near the torque output of impeller shaft 2011.The outer shroud of the second ball bearing 2023b is connected with the second end face of injection loop 2022 by Compress Spring 9, and Compress Spring 9 forms the preload of opposing rotor assembly 201 axial force.The relative distance between the inner ring of the first ball bearing 2023a and the inner ring of the second ball bearing 2023b is limited by distance ring 4 between the inner ring of the first ball bearing 2023a and the inner ring of the second ball bearing 2023b.The inner ring of the first ball bearing 2023a is imported into by impeller shaft 2011 moment of torsion holds the end face of side to be compressed by blower fan gear 2012 and locking nut 2013.The inner ring of the second ball bearing 2023b is close to layout by the end face of impeller shaft 2011 torque output side and disc 5.
As shown in Figure 1, Figure 2, shown in Fig. 3 and Fig. 5, in the present embodiment, axial flow compressor structure 1 comprise be located on air intake passage 3 exhaust outlet in order to by the air entered guiding Gas Turbine Generating Units 7 direction inlet guiding 101, in order to the air pressure that inlet guiding 101 is imported contract guiding Gas Turbine Generating Units 7 direction impeller 102 and be located at inlet guiding 101 and the outer field axial flow casing 103 of impeller 102.Inlet guiding 101 is fixed in axial flow casing 103 by axial flow outer shroud 6.Impeller 102 is arranged on the torque output of impeller shaft 2011 and rotates with impeller shaft 2011.
As depicted in figs. 1 and 2, in the present embodiment, seam between inlet casing 203 and axial flow casing 103, is adopted to locate and be connected and fixed by link.
As shown in Figure 2 and Figure 4, in the present embodiment, the pressurized air impeller shaft 2011 at the position that axial flow compressor structure 1 is connected with Gas Turbine Generating Units 7 is also provided with for being imported by impeller 102 carries out expansion supercharging and imports the exhaust section assembly 8 in Gas Turbine Generating Units 7.
As shown in Figure 2, in the present embodiment, the intake grill of air intake passage 3 is provided with the spiral case 10 increasing intake grill wind flow.
As shown in Figure 2, the Gas Turbine Generating Units of the present embodiment, comprises the above-mentioned cooling mechanism for Gas Turbine Generating Units.
During enforcement, cooling mechanism is for gas turbo-generator set provides the device of cooled gas, this device forces by air inlet volute (spiral case 10) the part clean air sucking unit gas handling system, by single-stage inlet guiding (inlet guiding 101 of the single blade of radial arrangement), through single-stage axial blade compresses, (rotor theoretical rotational speed is 34535r/min, this rotor separates a part of power by unit deceleration system and drives), finally by Tandem Blades To An Aeroengine assembly (the exhaust section assembly 8 of radial arrangement double-row blades), pressurized gas is led, expansion diffusion, an air part after compression is used for generator refrigeration, another part enters in crew compartment by the tap hole vertically upward of two in transfer passage, pressurized air flows through in cabin, take away the heat load of unit, finally go out cabin by engine high-temperature combustion gas by lobe jet pipe injection, ensure metastable unit normal operation circumstances.
Axial fan of the present invention adopts the structural type of single-stage axial compressor cell cube, as depicted in figs. 1 and 2.Stator part comprises inlet casing 203, neck bush 2021, injection loop 2022, inlet guiding 101, axial flow casing 103, axial flow outer shroud 6, exhaust section assembly 8.Adopt seam to locate between inlet casing 203 and axial flow casing 103, bolted structural type.Injection loop 2022, the structural type of radial pin between neck bush 2021 and inlet casing 203, is adopted to interfix.Interference fit is adopted between inlet casing 203 and neck bush 2021.Adopt small―gap suture to coordinate between injection loop 2022 with neck bush 2021, due to the existence of injection loop 2022 and neck bush 2021, former and later two ball bearings 2023 share a bearing bore, make oil system structure simpler.In rotor assembly 201 working procedure, axial force directly passes to inlet casing 203 by neck bush 2021, Path of Force Transfer advantages of simple.Located by cylndrical surface seam between inlet casing 203 and axial flow casing 103, and connected by 12 bolts, as shown in Figure 1.
Inlet guiding 101 includes inside and outside ring and guide vane.Inside and outside ring forms by aluminum alloy plate materials is bending.Guide vane totally 19.Guide vane is circumferentially distributed between the inside and outside ring of inlet guiding 101.Inside and outside ring and guide vane surface scribble zinc yellow expoxy ester primer, as shown in Figure 3.
Tandem Blades To An Aeroengine assembly (exhaust section assembly 8) forms by aluminum alloy plate materials is bending, and by being welded to connect, the design of the Tandem Blades To An Aeroengine of Tandem Blades To An Aeroengine assembly is the air outlet slit direction in order to change axial fan compression, make pressurized air along fan shaft to ejection, pressurized air is by the exhaust section cone cylinder expansion supercharging of Tandem Blades To An Aeroengine assembly.The exhaust section inside and outside ring of exhaust section assembly 8 and blade surface scribble zinc yellow expoxy ester primer, as shown in Figure 4.
Fan rotor part comprises locking nut 2013, blower fan gear 2012, impeller 102, impeller shaft 2011, is a kind of surperlight type rotor structure, can meet the density of load and the performance of high rotating speed lower rotor part, can reduce again size and the weight of blower fan.Impeller 102 and impeller shaft 2011 adopt the structural type that cylindrical interference is felt relieved, end face is located, oblique pin is connected, and connective stability is better, as shown in Figure 5.Fan rotor part adopts two ball bearing supporting, and front and back bearings all adopts three-point contact type inner ring to divide half angular contact ball bearing, and the neck bush 2021 be arranged in inlet casing 203 is inner, adopts rigidity 0-2-0 supporting form.Fore bearing outer shroud and injection loop 2022 end face are close to, by spacer, circlip and neck bush 2021 end face fix outer race.Rear bearing outer shroud is close to injection loop 2022 ear end face by Compress Spring 9, formed preload the axial force of resisting fan rotor, direction be following current road backward; Front and back bearings inner ring is supported by distance ring 4, fore bearing inner ring is compressed by blower fan gear 2012 and locking nut 2013, and by the torsion pass of blower fan gear 2012 internal spline, rear bearing inner ring is close to by disc 5, fan rotor part is close to disc 5 ear end face, as depicted in figs. 1 and 2.The moment of torsion inputted by blower fan gear 2012 is transferred to fan rotor part by spline, drives axial flow compressor high speed rotating, to air work, for providing refrigerant gas endlessly in cabin.
Structure is simple, volume is little, lightweight, reliability is high, and technology capability is good with assembling maintenance; Present invention employs the active heat removal mode of a kind of high efficiency forced convection cooling, rotor is by retarder terminal teeth wheel drive, rotation speed of fan can be regulated according to the changed power of unit, thus change cooling air quantity, make crew compartment environment relatively stable, the each element of unit normally works, and ensures the normal operation of gas turbo-generator set in power adjustment procedure.
Efficient forced-air cooling mechanism of the present invention, the utilization of axial fan in gas turbo-generator set, it is a kind of active heat removal mode.Force engine room ventilation by this device, take away the heat that combustion engine and generator produce in the course of the work, ensure the normal work of each element in unit.This axial fan adopts light design, and a large amount of employing aluminum alloy and titanium alloy component, as single-stage axial aluminum alloy integral blade disc, Shaft of Titanium Alloy, titanium alloy disc and aluminum alloy casing etc., decrease the weight of blower fan preferably.Axial fan does not change the flow direction of medium in runner, and flow resistance is little, and efficiency is high, and structural manufacturing process is simple and reliable, and volume is little, and quality is light, has enough range of safety operation.This axial fan can provide enough pressurized air to be generator refrigeration efficiently, ensures the stable operation of generator; Meanwhile, a part of pressurized air of being drawn by tap hole flows in cabin, ceaselessly takes away heat in cabin by different transfer of heat.The present invention initiates the active heat removal mode using convection current cooling, for unit provides cooled gas endlessly, takes away heat unnecessary in unit, thus serves vital effect to balancing machine indoor environment.
The foregoing is only the preferred embodiments of the present invention, be not limited to the present invention, for a person skilled in the art, the present invention can have various modifications and variations.Within the spirit and principles in the present invention all, any amendment done, equivalent replacement, improvement etc., all should be included within protection scope of the present invention.
Claims (9)
1., for a cooling mechanism for Gas Turbine Generating Units, it is characterized in that,
Comprise for Gas Turbine Generating Units (7) interior forced ventilation to take away the axial flow compressor structure (1) of heat and to drive in order to transmitting torque the driving mechanism (2) that described axial flow compressor structure (1) operates
Described driving mechanism (2) is connected with the output terminal of gas turbine drive case and links with the output terminal of gas turbine drive case;
Described axial flow compressor structure (1) and/or described driving mechanism (2) offer air intake passage (3);
Described driving mechanism (2) comprises in order to the rotor assembly (201) of driving torque, in order to support the stator assembly (202) of described rotor assembly (201) and to be located at described rotor assembly (201) and stator assembly (202) outer field inlet casing (203)
Described stator assembly (202) is fixed in described inlet casing (203),
Described stator assembly (202) is sheathed on described rotor assembly (201) outward.
2. the cooling mechanism for Gas Turbine Generating Units according to claim 1, is characterized in that,
Described rotor assembly (201) comprises in order to the impeller shaft (2011) of transmitting torque, in order to transmit the blower fan gear (2012) of gas turbine drive case output torque and the locking nut (2013) in order to fixing described blower fan gear (2012) to described impeller shaft (2011);
Described blower fan gear (2012) is locked on described impeller shaft (2011) by described locking nut (2013),
Described blower fan gear (2012) engages each other with the retarder end gear of described gas turbine drive case.
3. the cooling mechanism for Gas Turbine Generating Units according to claim 2, is characterized in that,
Described stator assembly (202) comprise for by the axial force transmission of described rotor assembly (201) to the neck bush (2021) of described inlet casing (203), in order to intercept the injection loop (2022) of lubricating oil and two in order to support the ball bearing (2023) of described impeller shaft (2011);
Interference fit is adopted to be connected between described neck bush (2021) with described inlet casing (203),
Described injection loop (2022) to be arranged between two described ball bearings (2023) and to adopt Spielpassung to be connected with described neck bush (2021),
Described ball bearing (2023), described neck bush (2021) and described injection loop (2022) surround a shared bearing bore.
4. the cooling mechanism for Gas Turbine Generating Units according to claim 3, is characterized in that,
Described ball bearing (2023) comprises the first ball bearing (2023a) and the second ball bearing (2023b);
Described first ball bearing (2023a) imports end layout near the moment of torsion of described impeller shaft (2011),
First end face of the outer shroud of described first ball bearing (2023a) and the first end face of described injection loop (2022) are close to layout,
Second end face of the outer shroud of described first ball bearing (2023a) is by spacer, circlip and described neck bush (2021) end face stationary positioned;
Described second ball bearing (2023b) is arranged near the torque output of described impeller shaft (2011),
The outer shroud of described second ball bearing (2023b) is connected with the second end face of injection loop (2022) by Compress Spring (9), and described Compress Spring (9) forms the preload of opposing described rotor assembly (201) axial force;
The relative distance between the inner ring of described first ball bearing (2023a) and the inner ring of described second ball bearing (2023b) is limited by distance ring (4) between the inner ring of described first ball bearing (2023a) and the inner ring of described second ball bearing (2023b)
The end face inner ring of described first ball bearing (2023a) being imported end side by described impeller shaft (2011) moment of torsion into is compressed by blower fan gear (2012) and locking nut (2013),
The inner ring of described second ball bearing (2023b) is close to layout by the end face of described impeller shaft (2011) torque output side and disc (5).
5. the cooling mechanism for Gas Turbine Generating Units according to claim 4, is characterized in that,
Described axial flow compressor structure (1) comprise be located on described air intake passage (3) exhaust outlet in order to the inlet guiding (101) in described Gas Turbine Generating Units (7) direction that the air entered is led, in order to the air pressure that described inlet guiding (101) is imported contract guiding described Gas Turbine Generating Units (7) direction impeller (102) and be located at described inlet guiding (101) and the outer field axial flow casing (103) of described impeller (102);
Described inlet guiding (101) is fixed in described axial flow casing (103) by axial flow outer shroud (6),
Described impeller (102) is arranged on the torque output of described impeller shaft (2011) and rotates with described impeller shaft (2011).
6. the cooling mechanism for Gas Turbine Generating Units according to claim 5, is characterized in that, adopts seam locate and be connected and fixed by link between described inlet casing (203) and described axial flow casing (103).
7. the cooling mechanism for Gas Turbine Generating Units according to claim 5, it is characterized in that, on the described impeller shaft (2011) at the position that described axial flow compressor structure (1) is connected with described Gas Turbine Generating Units (7), the pressurized air be also provided with for being imported by described impeller (102) carries out expansion supercharging and imports the exhaust section assembly (8) in described Gas Turbine Generating Units (7).
8. the cooling mechanism for Gas Turbine Generating Units according to any one of claim 1 to 7, is characterized in that, the intake grill of described air intake passage (3) is provided with the spiral case (10) increasing intake grill wind flow.
9. a Gas Turbine Generating Units, is characterized in that, comprises the cooling mechanism for Gas Turbine Generating Units according to any one of claim 1 to 8.
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| CN201410221711.1A CN103982302B (en) | 2014-05-23 | 2014-05-23 | For cooling mechanism and the Gas Turbine Generating Units of Gas Turbine Generating Units |
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| CN201410221711.1A CN103982302B (en) | 2014-05-23 | 2014-05-23 | For cooling mechanism and the Gas Turbine Generating Units of Gas Turbine Generating Units |
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| CN113123881B (en) * | 2019-12-31 | 2022-05-31 | 中国航发商用航空发动机有限责任公司 | Support structure of engine |
| CN113090392B (en) * | 2021-05-14 | 2022-01-07 | 中国航发湖南动力机械研究所 | Oil return and ventilation structure for transmission of aircraft engine accessories |
| CN113898419A (en) * | 2021-10-10 | 2022-01-07 | 中国航发沈阳发动机研究所 | Air inlet casing structure and assembling method thereof |
| CN114542294B (en) * | 2022-02-16 | 2024-06-18 | 中国航发沈阳发动机研究所 | High Mach number turbine engine central transmission system overall structure |
| CN115370612B (en) * | 2022-09-29 | 2023-04-21 | 江西中发天信航空发动机科技有限公司 | Axial-flow compressor rotor structure of aero-engine |
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| US2749087A (en) * | 1951-04-18 | 1956-06-05 | Bristol Aeroplane Co Ltd | Rotary machines |
| US3031128A (en) * | 1956-11-23 | 1962-04-24 | Rolls Royce | Gas-turbine engine with controllable air tapping means |
| JPH1047059A (en) * | 1996-08-06 | 1998-02-17 | Daihatsu Diesel Mfg Co Ltd | Ventilation device for gas turbine room |
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Also Published As
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|---|---|
| CN103982302A (en) | 2014-08-13 |
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Address after: Dong Jiaduan 412002 in Hunan province Zhuzhou city Lusong District Patentee after: AECC HUNAN AVIATION POWERPLANT Research Institute Country or region after: China Address before: Dong Jiaduan 412002 in Hunan province Zhuzhou city Lusong District Patentee before: CHINA AVIATION POWER MACHINERY INSTITUTE Country or region before: China |