CN1013214B - Single spool, two-stage high performance compress unit - Google Patents
Single spool, two-stage high performance compress unitInfo
- Publication number
- CN1013214B CN1013214B CN 90102576 CN90102576A CN1013214B CN 1013214 B CN1013214 B CN 1013214B CN 90102576 CN90102576 CN 90102576 CN 90102576 A CN90102576 A CN 90102576A CN 1013214 B CN1013214 B CN 1013214B
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- 210000000952 spleen Anatomy 0.000 description 3
- 230000008878 coupling Effects 0.000 description 2
- 238000010168 coupling process Methods 0.000 description 2
- 238000005859 coupling reaction Methods 0.000 description 2
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Abstract
The present invention relates to a gas generator of a gas turbine with a single rotor, which has the advantages of compact structure and high efficiency. The present invention uses a centrifugal primary compressor of double-size air intake, a centrifugal secondary compressor of single-side air intake, and a radial flow turbine to achieve the effect that the entire pressure ratio is larger than 15:1. The primary pressure ratio is two times larger than the secondary pressure ratio. The primary inlet Mach number is approximately larger than 1.4. The specific speed range of each compressor is approximately from 0.65 to 0.85. The specific speed range of a turbine is approximately from 0.50 to 0.75.
Description
The present invention relates to a kind of single spool, two-stage high performance compress unit.
At some, for example vehicle with and other require in the volume of motor is little, in light weight, rate of fuel consumption the is low application, the needs for as the gas-turbine power plant of the alternative of diesel engine obtain proof.Practical experience shows that it is to adopt conventional gas turbine to obtain that entity space and weight reduce.Yet when rated power reduced, it was the putative fact that the rate of fuel consumption of simple cycle motor degenerates, and was the major defect of existing device.
The way of attempting to obtain gas-turbine power plant in the past is to adopt the different structure of the centrifugal and footpath stream unit of many outfits always.For example, well-known gas turbine auxiliary power unit comprises the single face air inlet high pressure centrifugal gas compressor of a two-sided air inlet low pressure centrifugal-flow compressor and the work of a serial connection, so that required pressurized air and the outside venting of using of oil inflame in the firing chamber to be provided.Deliver to the drive pressure mechanism of qi and consistently with single-shaft engine in some sense use in the single-stage radial turbine that air horsepower output is provided from the high-temperature fuel gas of firing chamber for the outside.
Above-mentionedly can not provide enough pressure ratios, be summed up as rate of fuel consumption always obviously greater than the miniature power unit of the low-pressure ratio (promptly less than 12: 1) of equal-wattage high-speed diesel engine by satisfied component efficiencies.For to overcome in the effort of these restrictions, industrial typically adopt the centrifugal level of centrifugal-flow compressor in the end or two single face air inlets before one or more levels axial-flow compressor of employing, the conventional axial-flow turbine of the gas generator of these centrifugal compressors and motor is an one.For best 1000 horsepowers any gas turbine with these structures.Estimate that rate of fuel consumption is lower than 15: 1 situation in pressure ratio and is issued to about 0.45.
An object of the present invention is to provide a kind of centrifugal-flow compressor parts that radial-flow type formula turbine drives is complementary of adopting on same axle, employed single spool, two-stage high performance compress unit in the gas turbine gas generator of high pressure ratio.
In the existing small size gas turbine, rate of fuel consumption above-mentioned degenerates and is changed.In small size gas turbine, had big engine efficiency (the present invention is discussed below in detail) at present.Therefore, the gas turbine of simple cycle can be compared U.S. with 1000 horsepowers high-speed diesel engine at least aspect fuel consumption.So, the indicated prior art of conventional structure that the present invention adopts for all gas turbine companies has played progressive effect at the new context engine of developing.
The present invention roughly comprises a kind of flow passage structure of combustion gas wheel gas generator, characterizes (see figure 1) by following parts by the air-flow order:
1. as the first order, be essentially radial flow type double-entry compressor.
2. as partial, single face air inlet centrifugal-flow compressor.
3. as the gas generator turbine, radial turbine.
Adopt pressure ratio according to circulation according to the present invention,, for example under 4000 horsepowers of conditions, apply pressure to motor specifically in the lower-wattage scope apparently higher than conventional gas turbine.Because pressure ratio is one of principal element that efficient is exerted an influence, so will provide the thermal efficiency higher than existing gas turbine in the lower-wattage scope according to circulation of the present invention.
Another key property according to gas generator of the present invention is, by partly carefully regulating the distribution of pressure ratio between first and second grades, make first and second grades of gas compressors " coupling " utilize these interior gas compressors that mated of radial turbine directed driven " single face rotor ", and then make turbo machine, first order gas compressor and second level gas compressor all rotate with unequal angular velocity, at least obtain three significant advantages: first, the mechanical strength of radial-flow turbine, according to making all compressor parts be in the specific speed of the optimum state, be enough to make each centrifugal compressor under condition, to turn round near optimum value, second, the radial-flow turbine of working is under these conditions turning round near under the distinctive best specific speed value condition, and this revolution makes gas generator be in the optimum state.The 3rd, the high peripheral velocity that radial turbine obtains, the stagnation temperature that causes impacting the high-temperature fuel gas on turbine blade descends.As a result, turbine flows into temperature and can raise, with the further increase thermal efficiency or the operating life of turbine part can be prolonged.
According to the present invention, briefly to be narrated, the efficient gas turbine gas generator of this compact structure comprises can provide whole pressure ratio greater than 15: 1 compressor apparatus.This compressor apparatus comprises the two-sided air inlet centrifugal type air of a first order gas compressor with a pair of import and a shared outlet, with one with first order gas compressor neighbor configuration and have a second level single face air inlet centrifugal type air gas compressor that the suction port that communicates with the shared outlet of the first order also has second level outlet simultaneously, with one can make first and second grades to be mechanical type and to interconnect, the shaft assembly that can rotate with unequal angular velocity.This gas generator also comprises working off one's feeling vent one's spleen with the second level and is dynamically connected, to receive high-pressure air and to utilize high-pressure air to make oil inflame to produce the combusting room device of combustion gas.This gas generator still adopts a single-stage radial turbine with import and outlet, this turbine directly is connected with the shaft assembly drive unit, but also be connected with the combusting room device that receives air-flow at this turbine inlet place, the combustion gas demi-inflation drives first and second grades of gas compressors.Venting gas appliance is to link to each other with turbine outlet is pneumatic, is the combustion gas of demi-inflation of further expansion working so that carry.The pressure ratio of first order gas compressor is obviously greater than two times of second level gas compressor pressure ratio.The inflow Mach number of first order double-sided compressor is greater than 1.4, and the specific speed of first and second grades of gas compressors all approaches their optimum value and each is all greater than 0.60.
The whole pressure ratio of the gas generator of cross-over connection first and second stage compressors is more preferably greater than 20: 1, and when the pressure ratio of second level gas compressor was between 2: 1 and 4: 1, the pressure ratio of first order gas compressor was between 6: 1 and 9: 1.
Another optimum scheme is that the specific speed scope of each gas compressor is about 0.65-0.80, and the specific speed scope of turbine part is about 0.5-0.75 simultaneously, thereby the efficient of gas compressor and turbine is near their peak value.
Another optimum scheme is in the steady state running, and all high-pressure airs of first order output are received by second level gas compressor basically, and all high-pressure airs of second level gas compressor output are received by the firing chamber basically.
Also have, single face rotor of the present invention, the two-stage high performance compressor apparatus briefly comprises a double-entry compressor first order.
The single face air inlet centrifugal compressor second level, second level gas compressor are that pneumatic connection first order gas compressor is to receive the gas of its output.
Make all coaxial installation of the first order and second level gas compressor can be with one with the shaft assembly of the interdependent rotation of identical speed.All pressure ratios of whole compressor apparatus were greater than 15: 1, and the pressure ratio of first order gas compressor is greater than about two times of the pressure ratio of second level gas compressor, and the specific speed of first and second grades of gas compressors is all greater than 0.60.
Compressor apparatus preferably includes one and is installed on the shaft assembly, can be with the single-stage radial turbine of the identical speed driving first order and second level gas compressor, and the scope of the specific speed of this turbine is 0.50-0.75.
Among this explanation and the accompanying drawing that constitutes a specification part demonstrated one embodiment of the present of invention, be used for illustrating relevant principle of the present invention together with declaratives.
Fig. 1 is the cross sectional representation according to gas turbine gas generator of the present invention.
Fig. 2 A and 2B are the sketches of improved efficiency, and the improvement of efficient is because the result who adopts the specific speed of compressor part in the gas generator constructed in accordance and turbine components and these parts to be complementary.
Now, in conjunction with the accompanying drawings most preferred embodiment of the present invention is made explanation at large.
Gas generator of the present invention comprises can provide whole pressure ratio greater than 15: 1, and is equipped with the centrifugal low pressure compressor device of the two-sided air inlet first order of an a pair of import and a single outlet.As the following and described example of the present invention of Fig. 1, most preferred embodiment of the present invention is that the compressor apparatus 12 of this generator comprises first order low pressure compressor 14 by a kind of gas turbine gas generator shown in 10.First order gas compressor 14 comprises promisingly rotates shaft assembly 20 and the compressor rotor 18 of configuration and axially opposed in pairs respectively by the gas compressor peripheral component 16 of the two-sided air inlet of the flow passage shown in the arrow 22,24.First order gas compressor 14 also comprises housing 26 on every side, and it limits a pair of symmetry of the gas compressor blade chip module 32,34 of air on rotor 18 that makes and flows axial opposed import 28,30.The application case S.N577359 that is trying discloses a kind of the application's of being specially adapted to improved double-sided compressor.
Double-sided compressor assembly 16 has independent and the blower outlets 36 Diffuser assembly 38 pneumatic annular radial that are connected.Diffuser assembly 38 receives from exporting 36 high-speed airs that come out and high-speed air being transformed into the high pressure velocity air, so that be ultimately delivered to high-pressure compressor 40 and then deliver to firing chamber 60.Diffuser assembly 38 can leave the air hydrodynamic head of outlet 36 to keep a part with the displacement of manifold assembly (not shown).The application case SN577383 that is trying discloses a kind of diffuser system that changes geometrical shape, and this diffuser system can advantageously be used in the Diffuser assembly 38.
With reference to Fig. 1, Diffuser assembly 38 dispose one collect diffusion the annular air intake pressurized system 42 of air.For in the embodiment shown in Fig. 1, air intake pressurized system 42 and 44 pneumatic connections of crossing pipeline, 46 pneumatic connections of import air intake pressurized system of the high-pressure compressor 40 that pipeline 44 talks out with following meeting successively.Other crossing pipeline arranges that the structure that comprises the application case SN610580 narration of trying is can be adopted, and this kind structure provides supplementary structure and advantage component capabilities.
According to the present invention, compressor apparatus also comprises and approaches first order gas compressor and have an independent import and the independent second level high pressure centrifugal gas compressor of outlet.As the embodiment shown in following and Fig. 1, compressor apparatus 12 further comprises having the compressor inlet 50 of qualification, with what receive from the housing 48 of the high-pressure air of import air intake pressurized system 46, the high-pressure compressor 40 of single face entry radial formula gas compressor.This high-pressure compressor housing 48 is also limiting the second level blower outlet that passes through second level Diffuser assembly 56 and the 54 pneumatic connections of firing chamber supply air intake pressurized system.High-pressure compressor rotor 58 is configured in the housing 48, and is installed on the shaft assembly 20 so that rotate.Therefore the pressurized air flow passage is from the collection air intake pressurized system of double-sided compressor peripheral component 16, through the air intake pressurized system of crossing pipeline 44, enter the firing chamber by high-pressure compressor rotor 58 and supply with inlet plenum system 54 to the high-pressure compressor import.
In addition, according to the present invention, the selection of the pressure ratio of the first order and second level gas compressor is that pressure ratio in first low pressure stage is greater than about two times of the second high pressure stage pressure ratio.In addition, select the size of the flow passage of first order gas compressor will provide as following can the detailed description in detail, with the corresponding to suitable specific speed of pressure ratio of above-mentioned level selection.As in this embodiment, all cross over the pressure ratio of first and second grades of gas compressors approximately all greater than 15: 1, and the pressure ratio scope of its first order gas compressor 14 is about 6: 1 to 9: 1, and the pressure ratio scope of second level gas compressor 40 is about 2: 1 to 4: 1.Low relatively second level pressure ratio makes every effort to keep second level specific speed high as much as possible (face discussion as follows).
The inflow Mach number of this typical impeller tip is about 1.4 or bigger at first order compressor inlet 28,30 places, and occurs in the outside blade tip place of blade 32,34 leading edges when rated power operation.Though Mach number can produce shock wave at compressor inlet greater than 1.0, they are quite weak oblique shock waves, can seriously not influence all properties.Design basic principle of the present invention is, the specific speed of relevant controlling compressor part is more even more important than keeping low inflow Mach number, and this is a kind of change to conventional design practice in the prior art.
Pump, the component efficiencies of gas compressor and turbine depends on the selection of best specific speed to a great extent.This is the correlation of speed-flow-merit, and this pass ties up in the above-mentioned particular component the most effective transformation of energy is provided.Specific speed (Ns) is defined as follows:
Wherein: ω is the rotational velocity radian per second
Q is volumetric flow rate m
3/ second
△
HBe specific power watt/Kilograms Per Second
It has been found that, satisfy the requirement of the specific speed that two stage compressor is all suitable under the high pressure ratio condition of the present invention, it is crucial that the pressure ratio of first and second grades of gas compressors is distributed.Yet these two high advantages of accident are that all compressor part characteristics can make the radial turbine parts be near under its best specific speed condition and move.This coupling need not to adopt the single face rotor arrangement and realizes, gas compressor 14 and 40 is directly driven by turbine 66.These conditions provide the gas generator of the such high performance simple cycle of high efficiency of a kind of gas generator as shown in Figure 1.
According to the present invention, gas generator also comprises combusting room device, and it is dynamically connected the working off one's feeling vent one's spleen of second level gas compressor of oil inflame with being used for receiving high-pressure air and utilizing high-pressure air to produce combustion gas.As present embodiment, two firing chambers 60 are by double-walled turbine inlet manifold 62 and air intake pressurized system 54 pneumatic connections (firing chamber only is shown in Fig. 1).The quantity of firing chamber is not limit, as adopt the firing chamber of a plurality of no circulation cross sections in the application case SN610585 that is trying.When steady state is moved,, except that being used for cooling or sealing purpose, preferably, guide firing chamber 60 into through air intake pressurized system 54 with between manifold 62 each wall from all high-pressure airs that high stage compressor 40 comes out.
According to the present invention, gas generator also further comprises a single-stage radial turbine with an import and an outlet, this turbine is operation and connects, directly drive the shaft assembly that gas compressor is housed on it, and be pneumatic with the combusting room device of the combustion gas that can expand at this turbine inlet place receiving part and be connected.Pointed as present embodiment, gas generator 10 comprises that its turbine rotor 68 has the radial turbine 66 of the blade 70 of band blade tip 70a.This turbo machine 66 receives from the firing chamber 60 and comes out by the high-temperature fuel gas of turbine inlet nozzle assembly 72 through turbine inlet manifold 62.Turbine rotor 68 directly connects with shaft assembly 20, and the rotor 58 of high-pressure compressor 40 and the rotor 18 of low pressure compressor 14 are all rotated.The application case SN610580 that is trying provides the device feature that is specially adapted to shaft assembly 20.
According to the present invention, gas generator also comprises venting gas appliance, and working off one's feeling vent one's spleen of this venting gas appliance and turbo machine is dynamically connected so that the externally further expansion working of guide portion expansion combustion gas.Pointed as present embodiment, gas generator 10 comprises the manifold 74 that is the operation connection, so that receive the combustion gas of the demi-inflation of coming out from turbine, along line transportation to free turbine device 90 or free jet propulsion unit 92(Figure 1A), the burning and gas-exhausting work done that turbo machine 66 is come out is expanded.Free turbine device 90 can have one or more levels.(secondary has been shown among Fig. 1).
In Fig. 2, show the two stage compressor of the gas generator of design and the specific speed curve of radial turbine according to the present invention.All pressure ratios of this gas generator were greater than 20: 1, adopt pressure ratio to be about 9: 1, its inflow Mach number is about 3.5 greater than 1.4 double-entry compressor and pressure ratio: 1(is promptly little by 50% than the pressure ratio of the first order) second level single face air inlet centrifugal-flow compressor.Just as seen, the peak value of radial turbine efficient approaches two compressor stages peak value of efficient when the same axle as the gas generator constituent element turns round simultaneously.This is come out by " A " specified region representation in Fig. 2, and this zone comprises that the specific speed scope of gas compressor is about 0.65～0.85, and the specific speed scope of radial turbine is about 0.50～0.75.
Zone " B " is indicated, because alternative low pressure " first order " of supposition is to make according to the enlightenment of the high pressure ratio gas generator of prior art, and be connected to the second level centrifugal compressor of one or more axial flow levels or a single face air inlet centrifugal compressor, just in time drop under its optimum range.If Fig. 2 also indicated the radial-flow type gas generator turbine it have to and be complementary than the low specific speed gas compressor, will drop under its optimum range.In addition, because be to turn round under high and best specific speed condition according to the rotatable parts of all gas generator flow passages of the present invention, the actual size of each rotor diminishes and low cost.Also have, rotor assembly inertia diminishes, and can be easy to quick startup.
Two-sided air inlet first order gas compressor will provide the flow of the twice that is equivalent to have the single-entry compressor that can compare size.Under the steady state operating conditions, when air was compressed to design flow in the first order, the geometrical shape of the latter's flow passage can adapt to the whole first order and be compressed gas flow speed.Yet before when starting and first order volume flow reduced to design flow, second level gas compressor can " not exhaust " volume flow greater than design.
Therefore, preferably be provided in the device that aspirates under the starting conditions from the compressed air of first order gas compressor, remove the air that is sucked of second level gas compressor.As present embodiment pointed and in Fig. 1 with sketch drawing draw, suction channel 76 is to be connected with crossing pipeline 44, when valve 78 when when starting activates, receive compressed air from first order gas compressor 14.Shown automatic controller 80 and control valve 78, and manual operating device can be replaced controller 80.Those skilled in the art can easily select proper device, reach the function by the given controller 80 of the present invention.The air that is sucked can be discharged in as shown in Figure 1 the atmosphere simply.
There is profound difference between the present invention and the prior art.This structure provide one unexpected in being lower than 1000 horsepowers gas turbine, obtain first to be higher than 20: 1 pressure ratio may, this structure is the specific speed by certain limit, whole pressure ratio and another machinery and the pneumatic driving element that is complementary are to have described between first and second grades of gas compressors being connected of radial-flow type gas generator turbine, this may be that whole airplane engine and turbogenerator industry monitor always, in one piece of article that ROLLS Royce European Symposium delivers, being proved, the author of this piece article is PhilipG.Ruffles, autograph is " mini engine technology ", be published in Aeronautical Journal of the Royal Aeronautical Society, 1984.1～2.Wherein the pressure ratio to maximum prefetch phase of this motor is 14: 1～16: 1.
Because the possible high peripheral velocity of radial turbine, for example be 700 meter per seconds among the present invention, the stagnation temperature of the combustion gas of impact on turbine blade-tip 70a and the turbine metal temperature that therefore has are than the axial flow turbine temperature that is exposed to the same nozzle inlet temperature much lower (low 100～200 ℃).Therefore, the high tip speed of radial turbine among the present invention, owing to be subjected to the regulation of gas compressor requirement, in fact from the viewpoint of lower metal temperature, it has provided a kind of extra advantage.This just can combine with high pressure ratio of the present invention and adopt higher turbine inlet temperature (TIT), obtains very low rate of fuel consumption.High pressure ratio of the present invention circulation can obtain the high thermal efficiency during up to 1200 ℃ and need not to dispose cooling system in turbine rotor in the combustion temperature of working medium.Under the condition of this temperature, all existing axial-flow turbines all are to need cooling.When the pressure ratio of gas generator of the present invention more than 20: 1, further improve for making efficient, wish the radial turbine cooling or adopt nonmetallic rotor material, even the thermal efficiency can not be enhanced, also can cool off in order to improve specific power.
As present expect, the gas generator of in Fig. 1, being narrated can be ideally whole pressure ratio be 20: 1 about work, in air mass flow is that 40 Pounds Per Seconds and turbine inlet temperature (TIT) are higher than under 2200 the condition, generation is equivalent to 700 horsepowers air horsepower, has the thermal efficiency about 35% and adopts the gas generator expansion ratio of turbine to be about 5.0: 1.Turbine rotor speed is equivalent to about turbine blade-tip speed 750 meter per seconds near 92000rpm.Importantly be, this injected equivalent engine consumption rate is about 0.5～0.40 pound/horsepower/hour, and this value is equivalent to the gas generator of prior art heat exchange type gas turbine.Adopt the weight/power ratio of the motor of this gas generator only to be about 10% of comparability diesel engine weight/power ratio.
So far, the above-mentioned thermal efficiency just very big (promptly＞30000 horsepower) adopt axial flow type gas take turns or in less employing than low-pressure ratio and use and obtain in the power unit of heat exchanger/thermal accumulator.Certainly, low-speed diesel engine has the thermal efficiency preferably, still, sees it is obviously disadvantageous from the viewpoint of size and weight.
For those skilled in the art, obviously can make various remodeling to gas turbine fuel gas generator device of the present invention not deviating under the design prerequisite of the present invention.
Claims (8)
1, a kind of single spool, two-stage high performance compress unit comprises:
A two-sided air inlet centrifugal compressor first order,
A single face air inlet centrifugal compressor second level, this second level gas compressor is handled and is connected, with the gas of reception from above-mentioned first order gas compressor,
The shaft assembly that all coaxial installation of the first order and second level gas compressor is rotated with identical speed dependent,
It is characterized in that,
(a) all pressure ratios of crossing over compressor apparatus are greater than 15: 1,
(b) cross over the twice of the pressure ratio of described first order gas compressor greater than the described second level of leap gas compressor pressure ratio,
(c) described first and second grades of gas compressor specific speeds are all greater than 0.60.
2, compressor apparatus according to claim 1 is characterized in that each specific speed is the scope 0.65 to 0.85.
3, compressor apparatus according to claim 1, all pressure ratios that it is characterized in that compressor apparatus were greater than 20: 1.
4, compressor apparatus according to claim 2, all pressure ratios that it is characterized in that compressor apparatus were greater than 20: 1.
5, compressor apparatus according to claim 1 is characterized in that also comprising that the specific speed of described turbine-driven set is greater than 0.50 to the described first order and the equal turbine device that can drive of second level gas compressor.
6, compressor apparatus according to claim 5, the specific speed that it is characterized in that described turbine device is in 0.5 to 0.75 scope.
7, compressor apparatus according to claim 1, it is characterized in that also comprising can be to the first order and the equal turbine device that can drive of second level gas compressor, and described turbine-driven set is mounted on the shaft assembly, rotates with described identical speed.
8, compressor apparatus according to claim 1, it is characterized in that also comprising the turbine device that is used to drive the first order and second level gas compressor, described turbine-driven set is installed on the described shaft assembly, rotate with described identical speed, wherein compressor apparatus also comprises a single-stage radial turbine, this radial turbine is installed on the described shaft assembly, make the first order and second level gas compressor all with described identical speed driving, the specific speed of described turbo machine is in 0.5 to 0.75 scope.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 86105185 CN1010041B (en) | 1986-08-04 | 1986-08-04 | Dual entry radial turbine gas generator |
Related Parent Applications (2)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN86105185 Division | 1986-08-04 | ||
| CN 86105185 Division CN1010041B (en) | 1986-08-04 | 1986-08-04 | Dual entry radial turbine gas generator |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN1045842A CN1045842A (en) | 1990-10-03 |
| CN1013214B true CN1013214B (en) | 1991-07-17 |
Family
ID=4802759
Family Applications (2)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 86105185 Expired CN1010041B (en) | 1986-08-04 | 1986-08-04 | Dual entry radial turbine gas generator |
| CN 90102576 Expired CN1013214B (en) | 1986-08-04 | 1986-08-04 | Single spool, two-stage high performance compress unit |
Family Applications Before (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 86105185 Expired CN1010041B (en) | 1986-08-04 | 1986-08-04 | Dual entry radial turbine gas generator |
Country Status (1)
| Country | Link |
|---|---|
| CN (2) | CN1010041B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104500268A (en) * | 2014-12-12 | 2015-04-08 | 常州环能涡轮动力股份有限公司 | Micro turbine jet engine with two-sided centrifugal pressure roller |
-
1986
- 1986-08-04 CN CN 86105185 patent/CN1010041B/en not_active Expired
- 1986-08-04 CN CN 90102576 patent/CN1013214B/en not_active Expired
Also Published As
| Publication number | Publication date |
|---|---|
| CN1045842A (en) | 1990-10-03 |
| CN86105185A (en) | 1988-02-17 |
| CN1010041B (en) | 1990-10-17 |
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