CN104196638A - Floral axis and combustion gas turbine - Google Patents
Floral axis and combustion gas turbine Download PDFInfo
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- CN104196638A CN104196638A CN201410434497.8A CN201410434497A CN104196638A CN 104196638 A CN104196638 A CN 104196638A CN 201410434497 A CN201410434497 A CN 201410434497A CN 104196638 A CN104196638 A CN 104196638A
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Abstract
The invention discloses a floral axis and a combustion gas turbine. A first air inlet channel and a second air inlet channel which penetrate through the floral axis, are independent from each other and can be passed through by high pressure gas are axially arranged in the axial direction of the floral axis. One combustion gas turbine comprises a gas compressor and an impeller internally provided with a gas channel, and a rotating shaft at an air inlet end of the gas compressor is connected with a starting motor; one side of the floral axis is fixedly arranged in a cavity at the tail part of the gas compressor, the other side of the floral axis is fixedly connected with the end surface of one side of the impeller, and the cavity, the first air inlet channel, the gas channel and a waste gas discharging cavity are communicated to form a first gas flow channel; the cavity, the second air inlet channel and a cabin body at which the impeller is located are communicated to form a second gas flow channel; the end surface of the other side of the impeller is fixedly arranged on an output shaft; and a gas nozzle is formed in the second gas flow channel and an ignition device is arranged in the second gas flow channel.
Description
Technical field
The present invention relates to gas turbine technology field, be specifically related to a kind of floral axis and gas turbine.
Background technique
Gas turbine is that to take the gas of continuous-flow be working medium impeller High Rotation Speed, the energy of fuel is changed into the internal combustion type dynamic power machine of useful work, is the wheeled heat engine of a kind of pivoting leaf.
At present gas turbine on the market is mainly comprised of several major parts of gas compressor, firing chamber and combustion gas turbine, and during work, gas compressor, from ambient atmosphere environment air amount, and compresses step by step and makes it supercharging through gas compressor, also corresponding raising of air temperature simultaneously; Pressurized gas are pressed to firing chamber and burn and generate the combustion gas of High Temperature High Pressure with the fuel mix spraying into; And then enter into turbine expansion acting, promote turbine and drive gas compressor High Rotation Speed together with outer load rotor.
The pressurized gas that gas compressor enters account for 1/4～2/5 pressurized gas and enter burner inner liner front portion, the fuel oil gushing out with nozzle is mixed to form fuel-air mixture, through ignition device after-combustion, in pressurized gas, account for 3/4～3/5 from burner inner liner with inner room flow through, to burner inner liner wall, carry out cooling, a large amount of pressurized gas wastes, at least the efficiency of gas turbine is low.
Chemical energy is converted to the turbine of mechanical energy, complex structure; Combustion gas turbine rotating speed, up to tens thousand of turning per minute, needs resistant to elevated temperatures material to make in production process, and complex manufacturing technology.
Summary of the invention
For above shortcomings in prior art, the invention provides a kind of floral axis, it can make the pressurized gas that enter gas compressor divide two-way to pass through floral axis.
Aspect more of the present invention, provide a kind of floral axis, its technological scheme adopting is: this floral axis is multidiameter shaft, and at least two step sections of floral axis are axially arranged with and run through floral axis and separate the first gas-entered passageway passing through for pressurized gas and the second gas-entered passageway.
The present invention also provides a kind of gas turbine, and it adopts the floral axis of design and firing chamber and the turbine structure that impeller replaces conventional gas turbine, has improved working efficiency.
In other side, the invention provides a kind of gas turbine, comprise gas compressor, floral axis and the inner impeller that offers gas channel, on floral axis, be provided with twice separate and through the first gas-entered passageway and second gas-entered passageway of whole floral axis.One side of floral axis is fixedly mounted in the cavity of gas compressor afterbody, and the opposite side of floral axis is fixedly connected with impeller one side end face, and cavity, the first gas-entered passageway, gas channel and waste gas discharge side are communicated with formation the first gas flow; Cavity, the second gas-entered passageway and section cabin, impeller place body are communicated with formation the second gas flow; Impeller opposite side end face is fixedly mounted on output shaft; In the second gas flow, be provided with gas nozzle and ignition mechanism.
Beneficial effect of the present invention is: approximately have 1/5 ~ 1/2 pressurized gas in the fuel mix burning of the entrance front side of the second gas-entered passageway, the gas of expansion enters impeller clearance fast by the first gas-entered passageway; Or in the second gas-entered passageway suction side and fuel mix burning, enter fast impeller clearance, impeller fast rotational; The dynamic load of impeller band and gas compressor work;
In addition 1/2 ~ 4/5 not the pressurized gas of heating enter the first gas-entered passageway, in the inside of impeller, impeller is carried out in cooling by the gas-heated of impeller clearance, being expanded and spraying from impeller tip, impeller rotation; By to the making full use of of combustion gas and pressurized gas, during work, the thermal efficiency of gas turbine is up to 95%.
Adopt impeller simple in structure to replace turbine, floral axis simple in structure replaces firing chamber, the complete machine cost of the gas turbine of cutting interest rate.
Due to what flow in impeller clearance, be high-temperature expansion gas, impeller can be by heat temperature raising fast, and the not gas of heating of impeller internal flow can play certain cooling action to impeller, thereby has improved the working life of impeller.
Arrange after heat exchanger, pressurized gas can carry out heat exchange with the waste gas of discharging in heat exchanger, have reduced the loss of heat, have improved the thermal efficiency.
Accompanying drawing explanation
Fig. 1 is an embodiment's of floral axis half sectional view;
Fig. 2 is the right elevation of Fig. 1;
Fig. 3 is the left view of Fig. 1;
Fig. 4 is the sectional view of Fig. 1 A-A direction along the line;
Fig. 5 is the sectional view of Fig. 1 B-B direction along the line;
Fig. 6 is the sectional view of Fig. 1 C-C direction along the line;
Fig. 7 is the sectional view of Fig. 1 D-D direction along the line;
Fig. 8 is another embodiment's of floral axis half sectional view;
Fig. 9 is the right elevation of Fig. 8;
Figure 10 is the left view of Fig. 8;
Figure 11 is the sectional view of A type gas turbine;
Figure 12 is the sectional view of Type B gas turbine;
Figure 13 is the half sectional view that floral axis, impeller, inlet end panel and output shaft are fixedly installed togather;
Figure 14 is the sectional view at the online E-E of Figure 13 place;
Figure 15 is the sectional view of Figure 13 F-F direction along the line;
Figure 16 is the sectional view of C type gas turbine;
Figure 17 is the sectional view at the online H-H of Figure 16 place;
Figure 18 is the sectional view of D type gas turbine;
Figure 19 is an embodiment's of blade stereogram.
Wherein, 100, floral axis; 101, the First stage; 102, second step section; 103, the 3rd step section; 104, the 4th step section; 105, the first air flue; 106, the second gas-entered passageway; 107, mounting hole; 108, suction port; 109, the second air flue;
200, A type gas turbine; 201, inlet end panel; 202, impeller stiffening plate; 2021, mounting groove; 2022, axis hole; 203, waste gas discharge side; 204, impeller; 2041, top; 2042, air passing hole; 205, output shaft end panel; 206, black box; 207, bearing support; 208, output shaft; 209, shell; 210, ignition mechanism cable; 211, gas pipeline; 212, starter motor; 213, gas compressor; 214, coupling; 215, cavity;
300, Type B gas turbine; 301, heat exchange pipeline; 302, heat exchanger; 303, air-inlet cavity; 304, dividing plate; 305, refractory protection; 400, C type gas turbine; 401, cable protective sleeve; 402, ignition mechanism; 500, D type gas turbine.
Embodiment
Below the specific embodiment of the present invention is described; so that those skilled in the art understand the present invention; but should be clear; the invention is not restricted to the scope of embodiment; to those skilled in the art; as long as various variations appended claim limit and definite the spirit and scope of the present invention in, these variations are apparent, all utilize innovation and creation that the present invention conceives all at the row of protection.
On the floral axis 100 providing in one aspect of the invention, be provided with twice separate and be axially the first gas-entered passageway and the second gas-entered passageway through floral axis 100.
With reference to figure 1, Fig. 1 shows an embodiment's of floral axis of the present invention half sectional view, and as Fig. 1 to Fig. 6, the concrete structure of the floral axis of the present embodiment is:
This floral axis is multidiameter shaft, it comprises that the first air flue 105 that runs through floral axis 100 that the First stage 101, second step section 102 and the 3rd step section 103, the first gas-entered passageways that connect as one comprise that second step section 102 arranges and the 3rd step section 103 arrange is communicated with and runs through the second air flue 109 of floral axis 100 with the first air flue 105; The inlet end of the second gas-entered passageway 106 is arranged on the end face of the 3rd step section 103.
With reference to figure 1 and Fig. 7, in one embodiment of the invention, floral axis 100 can also comprise the 4th step section 104 being integrated in succession with the 3rd step section 103, is provided with some screw holes that are connected with other structures (such as impeller 204 or inlet end panel 201) in the 4th step section 104.Wherein, the diameter of floral axis 100 increases gradually from First stage 101 to the 4th step section 104, is also First stage diameter < second step section diameter < the 3rd step section diameter < the 4th step section diameter.
In one embodiment of the invention, with reference to figure 8, to Figure 10, at floral axis 100 center, be provided with the mounting hole 107 that runs through floral axis 100, and on the First stage 101, offer some suction ports 108 that are communicated with mounting hole 107.
Based on essentially identical design, the invention provides the gas turbine of several different structures, it is respectively A type gas turbine 200, Type B gas turbine 300, C type gas turbine 400 and D type gas turbine 500, but the gas turbine based on the present invention's design does not limit to and above-mentioned four.
Below with reference to Fig. 1 to Fig. 7 and Figure 11, A type gas turbine 200 is described:
As shown in figure 11, in structures more of the present invention, A type gas turbine 200 comprises gas compressor 213, floral axis 100 and the inner impeller 204 that offers gas channel, and the rotating shaft of gas compressor 213 inlet ends is connected with starter motor 212; One side of floral axis 100 is fixedly mounted in the cavity 215 of gas compressor 213 afterbodys, particularly, the First stage 101 of floral axis 100 is connected with the rotating shaft of gas compressor 213 afterbodys by coupling 214, at coupling 214, away from a side of floral axis 100, bearing support 207 is installed, gas compressor 213 is connected with shell 209 by the supporting base in the shell of bearing support 207 and gas turbine.
The opposite side of floral axis 100 is fixedly connected with impeller 204 1 side end faces, particularly, impeller 204 is fixedly installed togather with the 3rd step section 103 of floral axis 100, but in order to increase the lifting surface area of impeller 204 and floral axis 100 joints, between impeller 204 and floral axis 100, an inlet end panel 201 can be set, the 3rd step section 103 of floral axis 100 is fixedly mounted on inlet end panel 201 by screw, also the end face of the 3rd step section 103 of floral axis 100 can be welded on inlet end panel 201.The end face of impeller 204 is welded on inlet end panel 201, and the first gas-entered passageway, gas channel are communicated with cavity 215 with the waste gas discharge side 203 of impeller end; The second gas-entered passageway 106 is communicated with cavity 215 and impeller 204 section cabin, place bodies.
In one embodiment of the invention, when floral axis 100 is also provided with a 4th step section 104 connecting as one with the 3rd step section 103, impeller 204 is fixedly installed togather with the 4th step section 104 of floral axis 100, but in order to increase the lifting surface area of impeller 204 and floral axis 100 joints, between impeller 204 and floral axis 100, an inlet end panel 201 can be set, the 4th step section 104 of floral axis 100 is fixedly mounted on inlet end panel 201 by screw, also the end face of the 4th step section 104 of floral axis 100 can be welded on inlet end panel 201; The end face of impeller 204 is welded on inlet end panel 201.
Impeller 204 opposite side end faces are fixedly mounted on output shaft 208; Particularly, end near impeller 204 on output shaft 208 is provided with output shaft end panel 205, output shaft end panel 205 can be one-body molded with output shaft 208, after also can processing, is welded on output shaft 208, and the opposite side of impeller 204 is welded on output shaft end panel 205.Bearing support 207 is installed on the end at output shaft 208 away from output shaft end panel 205.
In the cavity 215 in the second gas-entered passageway 106 outsides of floral axis 100, be provided with gas pipeline 211 and ignition mechanism cable 210, wherein the nozzle on gas pipeline 211 and the ignition mechanism 402 on ignition mechanism cable 210 are in alignment with the gas entry port of the second gas-entered passageway 106, and the gas entry port of nozzle and ignition mechanism 402 and the second gas-entered passageway 106 is infinitely contiguous, can guarantee that like this combustion gas and the pressurized gas lighted enter impeller 204 place section impeller 204 rotations by the second gas-entered passageway 106 rapidly.
With reference to Figure 14 and Figure 19, in one embodiment of the invention, impeller 204 can be comprised of some blades, blade interior is hollow structure, the top 2041 of blade and at least one side end face are provided with the air passing hole 2042 being communicated with hollow structure, and gas channel consists of the hollow structure on all blades and the air passing hole 2042 that is communicated with hollow structure.
Blade pass is crossed the end face that is provided with air passing hole 2042 and is fixedly connected with floral axis 100, the cooled gas that enters the first gas-entered passageway enters the inside of blade by the air passing hole 2042 of a side end face setting of blade, blade to high-temperature gas heating plays certain cooling action, the heat that cooling pressurized gas are passed to by blade simultaneously adds thermal expansion and further promotes blade rotary, and the gas of expansion enters waste gas discharge side 203 from the air passing hole 2042 at the top 2041 of impeller 204.
In one embodiment of the invention, at the gas inlet place of the second gas-entered passageway 206 end face, be provided with the refractory protection 305 that floral axis end face is protected.
Because blade is to be welded on floral axis 100 and output shaft 208 or two end faces of blade are welded on respectively on inlet end panel 201 and output shaft end panel 205 by two end faces, at impeller 204, run up in process, stressed possibility between each blade is inhomogeneous, for this reason, as shown in FIG. 13 to 15, in one embodiment of the invention, blade middle part is at least provided with an impeller stiffening plate 202 that all blades are coupled together.
As shown in figure 16, be wherein provided with on impeller stiffening plate 202 some for the mounting groove 2021 of blade is installed.In order further to guarantee stressed uniformity between each blade to be provided with an axis hole 2022 at the middle part of each impeller stiffening plate 202, impeller stiffening plate 202 can be arranged on output shaft 208 by the axis hole 2022 of its setting.
Waste gas discharge side 203 on the housing of gas compressor 213 afterbodys to the cavity in output shaft end panel 205 place section settings the First stage 101 of floral axis 100, second step section 102, the 3rd step section 103, the 3rd step section 104, impeller 204, impeller stiffening plate 202 and output shaft end panel 205 are wrapped in; Arranging of waste gas discharge side 203 can guarantee to be disposed in atmosphere after the unified processing of the waste gas of discharging.
A type gas turbine 200 working principles are: start A type gas turbine 200, gas compressor 213 is first under the drive of starter motor 212, air is compressed, gas after compression enters the cavity 215 of gas compressor 213 tail ends, the passage that pressurized gas divide two-way to enter floral axis 100, one tunnels approximately has 1/5 ~ 1/2 pressurized gas to carry out through the second gas-entered passageway 106, cavity 215 and impeller 204 section cabin, place bodies being communicated with after mixed expanded in the second gas-entered passageway 106 entry ports and the combustion gas of lighting promotes impeller 204 fast rotational;
The pressurized gas that does not heat on another road 1/2 ~ 4/5 are communicated with cavity 215 in the passage forming with the waste gas discharge side 203 of impeller end through the first gas-entered passageway, gas channel, to 204 certain cooling actions of the impeller by high-temperature expansion gas-heated, give simultaneously 204 1, impeller with impeller clearance mesohigh gas to the identical power of the rotating force of impeller; Thereby the power band dynamic load producing by impeller 204 and gas compressor 213 work.
After the normal rotation of impeller 204, impeller 204 can drive gas compressor 213 work, so just can not need starter motor 212 to provide power for gas compressor 213, so close motivation 212 after impeller 204 is normally worked.
Below with reference to Fig. 1 to Fig. 7 and Figure 12, Type B gas turbine 300 is described:
For making full use of of heat in the waste gas that waste gas discharge side 203 is discharged, the Type B gas turbine 300 of the present embodiment is on the basis of A type gas turbine 200, to have increased a heat exchanger 302, the cavity 215 of gas compressor 213 tail ends has been done to some little adjustment simultaneously.
Concrete technological scheme is that heat exchanger 302 is communicated with waste gas discharge side 203; A dividing plate 304 is installed on floral axis 100, and cavity 215 is separated into the first cavity and the second cavity by the dividing plate 304 of installing on floral axis 100; The housing of gas compressor 213 is outside equipped with the air-inlet cavity 303 being communicated with the first cavity; Heat exchange pipeline 301 in heat exchanger 302 is communicated with air-inlet cavity 215 with the second cavity; The second cavity is communicated with the first gas-entered passageway.
As shown in figure 12, in one embodiment of the invention, dividing plate 304 can be arranged in the second step section 102 of floral axis 100, and between dividing plate 304 and floral axis 100, black box 206 is set, to avoid the gas heating through waste gas again to flow in first cavity in dividing plate 304 left sides.
In one embodiment of the invention, between the gas turbine housing of formation waste gas discharge side 203 and floral axis 100 and between the gas turbine housing of formation waste gas discharge side 203 and output shaft 208, be provided with black box 206, the black box 206 at this two place can be guaranteed the sealing of waste gas discharge side 203.
300 machine working principles are taken turns in Type B combustion gas: start Type B gas turbine 300, gas compressor 213 is first under the drive of starter motor 212, air is compressed, gas after compression enters the cavity 215 of gas compressor 213 tail ends, the passage that pressurized gas divide two-way to enter floral axis 100, the first cavity Zhong You mono-tunnels approximately has 1/5 ~ 1/2 pressurized gas to carry out through the second gas-entered passageway 106, the first cavity and section cabin, impeller place body being communicated with after mixed expanded in the second gas-entered passageway 106 entry ports and the combustion gas of lighting promotes impeller 204 fast rotational;
The pressurized gas that in the first cavity, does not heat on another road 1/2 ~ 4/5 enter the heat exchange pipeline 301 in heat exchanger 302 through air-inlet cavity 303, carry out entering the second cavity after heat exchange with the waste gas in heat exchanger 302, enter via the second cavity, the first gas-entered passageway, gas channel and the second cavity is communicated with to the passage forming with the waste gas discharge side 203 of impeller end, to 204 certain cooling actions of the impeller by high-temperature expansion gas-heated, give 204 1, impeller and the power of impeller clearance mesohigh gas to the rotating force equidirectional of impeller simultaneously; Thereby the power band dynamic load producing by impeller 204 and gas compressor 213 work.
After the normal rotation of impeller 204, impeller 204 can drive gas compressor 213 work, so just can not need starter motor 212 to provide power for gas compressor 213, so close motivation 212 after impeller 204 is normally worked.
Below with reference to Fig. 8 to Figure 10 and Figure 16, Figure 17, C type gas turbine 400 is described:
Because A type gas turbine 200 and Type B gas turbine 300 are all after combustion gas is lighted in gas inlet place of the second gas-entered passageway 106 of floral axis 100, after mixing with pressurized gas, enter again the second gas-entered passageway 106, also the gas that enters the second gas-entered passageway 206 is high-temperature expansion gas, and this just requires floral axis 100, impeller 204 all to adopt high temperature resistant material to make with impeller stiffening plate 202.
For this reason, the C type gas turbine 400 of the present embodiment is, on the basis of A type gas turbine 200, appropriate adjustment has been carried out in the mounting point of ignition mechanism cable 210 and gas pipeline 211, and concrete technological scheme is:
In floral axis 100 central positions, offer the mounting hole 107 that runs through floral axis 100, in the rotating shaft of gas compressor 213, offer a through hole, gas pipeline 211 and ignition mechanism cable 210 are arranged in above-mentioned mounting hole 107 and through hole, ignition mechanism 402 on the nozzle of gas pipeline 211 and ignition mechanism cable 210 is arranged on to impeller 204 section cabin, place bodies, and the end face of nozzle and ignition mechanism 402 infinite approachs and floral axis 100 low order end sides.
In one embodiment of the invention, nozzle and ignition mechanism cable 210 are preferably arranged on the outlet port of the second gas-entered passageway 106, the pressurized gas that combustion gas just can be come with conveying after lighting like this mix, and make pressurized gas impeller 204 fast rotational that expand rapidly.
Because gas turbine is when working, gas compressor 213 and floral axis 100 all can rotate rapidly, for fear of the fast rotational of gas compressor 213 and floral axis 100, damage the gas pipeline 211 and ignition mechanism cable 210 arranging in mounting hole 107 and through hole, in one embodiment of the invention, in through hole and the interior bearing that restriction gas pipeline 211 and ignition mechanism cable 210 rotations are all at least installed of mounting hole 107.
Heated expanding gas may flow backwards along the mounting hole 107 in floral axis 100, the gas pipeline 211 of the inside of floral axis 100 and ignition mechanism cable 210 are heated, gas pipeline 211 and ignition mechanism cable 210 are damaged in high-temperature heating situation, in one embodiment of the invention, on floral axis 100, be provided with some suction ports 108 that the first cavity and mounting hole 107 is communicated with, after arranging like this, not heated pressurized gas can be to the interior close heated gas pipeline 211 of mounting hole 107 and 210 certain cooling actions of ignition mechanism cable.
Preferably suction port 108 was opened on the First stage 101 of floral axis 100, at the contiguous rotating shaft end of floral axis 100, and the mounting hole 107 that is positioned at suction port 108 left sides is provided with leak jacket, leak jacket can avoid the not heated pressurized gas that enter by suction port 108 to the external world, to flow out in through hole, can block the high pressure expanding gas entering in mounting hole 107 and enter in through hole simultaneously.
C type gas turbine 400 working principles are: start C type gas turbine 400, gas compressor 213 is first under the drive of starter motor 212, air is compressed, gas after compression enters the cavity 215 of gas compressor 213 tail ends, pressurized gas divide two-way to enter floral axis 100, one tunnel approximately has 1/5 ~ 1/2 pressurized gas to enter passage cavity 215 and impeller 204 section cabin, place bodies being communicated with through the second gas-entered passageway 106, and carries out after mixed expanded promoting impeller 204 fast rotational with the combustion gas of lighting in the second gas-entered passageway 106 outlet ports;
The pressurized gas that does not heat on another road 1/2 ~ 4/5 are communicated with cavity 215 in the passage forming with the waste gas discharge side 203 of impeller 204 ends through the first gas-entered passageway, gas channel, to 204 certain cooling actions of the impeller by high-temperature expansion gas-heated, give simultaneously 204 1, impeller with impeller clearance mesohigh gas to the identical power of the rotating force of impeller; Thereby the power band dynamic load producing by impeller 204 and gas compressor 213 work.
After the normal rotation of impeller 204, impeller 204 can drive gas compressor 213 work, so just can not need starter motor 212 to provide power for gas compressor 213, so close motivation 212 after impeller 204 is normally worked.
With reference to Figure 17, in one embodiment of the invention, at the outer surface of ignition mechanism cable 210, be also enclosed with one deck cable protective sleeve 401, can prevent that like this ignition mechanism cable 210 from being damaged by high-temperature gas.
Below with reference to Fig. 8 to Figure 10 and Figure 17, Figure 18, D type gas turbine 500 is described:
For making full use of of heat in the waste gas that waste gas discharge side 203 is discharged, the D type gas turbine 500 of the present embodiment is on the basis of C type gas turbine 400, to have increased a heat exchanger 302, the cavity 215 of gas compressor 213 tail ends has been done to some little adjustment simultaneously.
Concrete technological scheme is that heat exchanger 302 is communicated with waste gas discharge side 203; A dividing plate 304 is installed on floral axis 100, and cavity 215 is separated into the first cavity and the second cavity by the dividing plate 304 of installing on floral axis 100; The housing of gas compressor 213 is outside equipped with the air-inlet cavity 303 being communicated with the first cavity; Heat exchange pipeline 301 in heat exchanger 302 is communicated with air-inlet cavity 303 with the second cavity; The second cavity is communicated with the first gas-entered passageway.
As shown in figure 12, in one embodiment of the invention, dividing plate 304 can be arranged on the second step section 102 of floral axis 100, and between dividing plate 304 and floral axis 100, black box 206 is set, to avoid the gas heating through waste gas again to flow in first cavity in dividing plate 304 left sides.
In one embodiment of the invention, between the gas turbine housing of formation waste gas discharge side 203 and floral axis 100 and between the gas turbine housing of formation waste gas discharge side 203 and output shaft 208, be provided with black box 206, the black box 206 at this two place can be guaranteed the sealing of waste gas discharge side 203.
D type gas turbine 500 working principles are: start D type gas turbine 500, gas compressor 213 is first under the drive of starter motor 212, air is compressed, gas after compression enters the cavity of gas compressor 213 tail ends, pressurized gas divide two-way to enter floral axis 100, in the first cavity, approximately there are 1/5 ~ 1/2 pressurized gas to enter the passage the first cavity and impeller 204 section cabin, place bodies being communicated with through the second gas-entered passageway 106, and carry out after mixed expanded promoting impeller 204 fast rotational with the combustion gas of lighting in the second gas-entered passageway 106 outlet ports;
The pressurized gas that in the first cavity, does not heat on another road 1/2 ~ 4/5 enter the heat exchange pipeline 301 in heat exchanger 302 through air-inlet cavity, carry out entering the second cavity after heat exchange with the waste gas in heat exchanger 302, enter via the second cavity, the first gas-entered passageway, gas channel and the second cavity is communicated with to the passage forming with the waste gas discharge side 203 of impeller end, to 204 certain cooling actions of the impeller by high-temperature expansion gas-heated, give simultaneously 204 1, impeller with impeller clearance mesohigh gas to the identical power of the rotating force of impeller; Thereby the power band dynamic load producing by impeller 204 and gas compressor 213 work.
After the normal rotation of impeller 204, impeller 204 can drive gas compressor 213 work, so just can not need starter motor to provide power for gas compressor 213, so close motivation 212 after impeller 213 is normally worked.
Although by reference to the accompanying drawings the specific embodiment of the present invention is described in detail, should not be construed as the restriction to the protection domain of this patent.In the described scope of claims, the various modifications that those skilled in the art can make without creative work and distortion still belong to the protection domain of this patent.
Claims (11)
1. a floral axis, is characterized in that, this floral axis is multidiameter shaft, and at least two step sections of described floral axis are axially arranged with and run through floral axis and separate the first gas-entered passageway passing through for pressurized gas and the second gas-entered passageway.
2. floral axis according to claim 1, is characterized in that, described floral axis comprises First stage, second step section and the 3rd step section connecting as one; Described the first gas-entered passageway comprises and is arranged in described second step section and runs through the first air flue of described floral axis and be arranged at the second air flue that the first air flue described in described the 3rd step Duan Shangyu is communicated with and runs through described floral axis; The inlet end of described the second gas-entered passageway is arranged on the end face of the 3rd step section.
3. floral axis according to claim 1 and 2, is characterized in that, the center of described floral axis is provided with the mounting hole that runs through described floral axis.
4. a gas turbine that comprises floral axis described in claim 1 or 2, is characterized in that, comprises gas compressor and the inner impeller that offers gas channel; One side of described floral axis is fixedly mounted in the cavity of gas compressor afterbody, the opposite side of described floral axis is fixedly connected with described impeller one side end face, and described cavity, described the first gas-entered passageway, described gas channel and waste gas discharge side are communicated with formation the first gas flow; Described cavity, the second gas-entered passageway and section cabin, described impeller place body are communicated with formation the second gas flow; Described impeller opposite side end face is fixedly mounted on output shaft; In described the second gas flow, be provided with gas nozzle and ignition mechanism.
5. gas turbine according to claim 4, is characterized in that, described gas nozzle and described ignition mechanism are arranged on contiguous described the second gas-entered passageway gas entry port place of described cavity; Described gas nozzle is connected with the gas pipeline that passes the housing of gas compressor.
6. gas turbine according to claim 5, is characterized in that, also comprises the heat exchanger being communicated with described waste gas discharge side; The baffle for separating that described cavity is installed on floral axis becomes the first cavity and the second cavity; The housing of described gas compressor is outside equipped with the air-inlet cavity being communicated with the first cavity; Heat exchange pipeline in described heat exchanger is communicated with described air-inlet cavity with described the second cavity; Described the second cavity is communicated with described the first gas-entered passageway.
7. gas turbine according to claim 4, is characterized in that, described gas nozzle and described ignition mechanism are arranged on contiguous the second gas-entered passageway gas outlet of section cabin, described impeller place body; The center of described floral axis is provided with the mounting hole that runs through described floral axis; In the rotating shaft of described gas compressor, offer through hole, described through hole with in mounting hole, be provided with and the gas pipeline that described gas nozzle is communicated with and the ignition mechanism cable being connected with described ignition mechanism.
8. gas turbine according to claim 7, is characterized in that, also comprises the heat exchanger being communicated with described waste gas discharge side; The baffle for separating that described cavity is installed on floral axis becomes the first cavity and the second cavity; The housing of described gas compressor is outside equipped with the air-inlet cavity being communicated with the first cavity; Heat exchange pipeline in described heat exchanger is communicated with described air-inlet cavity with described the second cavity; Described the second cavity is communicated with described the first gas-entered passageway.
9. according to the arbitrary described gas turbine of claim 4-8, it is characterized in that, described impeller is comprised of some blades, blade interior is hollow structure, and the top of blade and at least one side end face are provided with the air passing hole being communicated with hollow structure, described blade pass is crossed the end face that is provided with air passing hole and is fixedly connected with described floral axis.
10. gas turbine according to claim 9, is characterized in that, described blade middle part is at least provided with an impeller stiffening plate that all blades are coupled together.
11. according to is characterized in that described in claim 7 or 8, and the bearing of a restriction gas pipeline and the rotation of ignition mechanism cable is all at least installed in described through hole and in mounting hole.
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| CN201410434497.8A CN104196638B (en) | 2014-08-29 | 2014-08-29 | A kind of floral axis and gas turbine |
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| CN201410434497.8A CN104196638B (en) | 2014-08-29 | 2014-08-29 | A kind of floral axis and gas turbine |
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| CN104196638A true CN104196638A (en) | 2014-12-10 |
| CN104196638B CN104196638B (en) | 2015-12-02 |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1524259A (en) * | 1976-11-12 | 1978-09-06 | Lewis V D | Turbines |
| CN2177811Y (en) * | 1993-07-21 | 1994-09-21 | 张士维 | Turbine |
| WO2012129579A1 (en) * | 2011-03-24 | 2012-09-27 | French Ian Eugene | Engine |
| GB2491586A (en) * | 2011-06-06 | 2012-12-12 | Vito Lozupone | An internal jet rotary engine |
| CN204212861U (en) * | 2014-08-29 | 2015-03-18 | 孙朝宽 | A kind of floral axis and gas turbine |
-
2014
- 2014-08-29 CN CN201410434497.8A patent/CN104196638B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1524259A (en) * | 1976-11-12 | 1978-09-06 | Lewis V D | Turbines |
| CN2177811Y (en) * | 1993-07-21 | 1994-09-21 | 张士维 | Turbine |
| WO2012129579A1 (en) * | 2011-03-24 | 2012-09-27 | French Ian Eugene | Engine |
| GB2491586A (en) * | 2011-06-06 | 2012-12-12 | Vito Lozupone | An internal jet rotary engine |
| CN204212861U (en) * | 2014-08-29 | 2015-03-18 | 孙朝宽 | A kind of floral axis and gas turbine |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104196638B (en) | 2015-12-02 |
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