CN1011064B - Gas turbine combustor - Google Patents
Gas turbine combustorInfo
- Publication number
- CN1011064B CN1011064B CN 88106413 CN88106413A CN1011064B CN 1011064 B CN1011064 B CN 1011064B CN 88106413 CN88106413 CN 88106413 CN 88106413 A CN88106413 A CN 88106413A CN 1011064 B CN1011064 B CN 1011064B
- Authority
- CN
- China
- Prior art keywords
- mixed gas
- mentioned
- main
- fuel
- gas turbine
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D23/00—Assemblies of two or more burners
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
- F23D14/26—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid with provision for a retention flame
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
Abstract
This invention relates to a gas turbine combustor of a premixing combustion system in which a fuel and the air are mixed and burnt, consisting of a cylindrical main nozzle provided on an upstream end wall of a cylindrical combustion chamber, an auxiliary nozzle formed around the main nozzle, a main premixed gas supply means for supplying a premixed gas to the main nozzle, and an auxiliary premixed gas supply means for supplying a premixed gas, the excess air ratio of which is smaller than that of the main premixed gas, to the auxiliary nozzle. Owing to this arrangement, a lean premixed gas having an excess air ratio larger than 1 can be burnt stably under low to high loads of a gas turbine.
Description
The present invention relates to gas turbine burner, specifically, relate to a kind of like this gas turbine burner, after it is pre-mixed fuel and combustion air, form pre-mixed gas, this pre-mixed gas is burnt in the mixed combustion mode.
In general, in gas turbine burner, when burning contains the gaseous fuel of small amount of nitrogen, when for example burning liquefied natural gas, most of nitrogen oxide of generation is the hot nitrogen oxide that is generated by the oxidized back of the nitrogen in the combustion air in high temperature air.The growing amount of this hot nitrogen oxide greatly depends on temperature, and increases along with increasing of flame temperature.Particularly when flame temperature surpassed 1500 ℃, its growing amount increased sharp.Flame temperature is with fuel and Air mixing ratio, promptly changes with so-called air-fuel ratio.In order to make fuel completing combustion, so that neither the air capacity of excessive non-deficiency again (theoretical air requirement) made this fuel combustion, when promptly making its burning with so-called chemically correct fuel, it is the highest that flame temperature becomes.
Thereby, in order to suppress the growing amount of nitrogen oxide, be necessary to reduce flame temperature.For this reason, can in the combustion chamber, send into water or steam, forcibly reduce flame temperature, perhaps use the combustion air amount more much more to burn than theoretical air requirement, perhaps use the combustion air amount of lacking than theoretical air requirement to burn, thereby reduce flame temperature.
But when sending into water or steam in the combustion chamber, Efficiency of Steam Turbine descends, the new problem that Here it is has produced.
In addition, in common burner, fuel and air are sent in the combustion chamber by nozzle separately respectively, both mixed and burnings in the combustion chamber.At this moment, the burning of so-called diffusion flame taking place, in both mixed processes, exist excess air ratio (combustion air amount/theoretical air requirement) to approach 1 zone, promptly exists to have the zone of approaching a kind of like this air-fuel ratio of chemically correct fuel.As previously mentioned, the flame temperature in this zone uprises partly, and the nitrogen oxide that produces is also a lot.
In contrast, such burner is arranged also, it is pre-mixed fuel and air and forms pre-mixed gas, sends into then in the burner and makes its burning.In this occasion, carrying out so-called premixed flame burning.When premixed flame burns, can use the combustion air (excess air ratio is more than 1) of Duoing to make its burning than theoretical air requirement.That is, can make its burning with thin air-fuel ratio.Thereby, can avoid having the zone of approaching chemically correct fuel, avoid the zone that the ignition temperature part uprises.Like this, just can suppress the generation of nitrogen oxide.But premixed flame equally also is near theory air-fuel ratio combustion the time, and it is the most stable that promptly excess air ratio approaches burning in 1 o'clock.In addition, when the spouting velocity of pre-mixed gas accelerated, flame became and is easy to be blown out, and on the contrary, when spouting velocity was slow, flame blowed back in the nozzle easily, promptly is easy to generate back-fire.In order to prevent back-fire, in gas turbine burner, generally, pre-mixed gas is sent in the burner with the spouting velocity of 50 meter per seconds.But, when sending into pre-mixed gas, be difficult to form flame with high like this spouting velocity.
Therefore, open shown in the clear 61-22127 file, adopted the burner of diffusion flame burning and premixed flame burning and usefulness as the spy.It is a kind of like this burner, and its uses by more stable diffusion flame or the high temperature air that generated by diffusion flame, and the pre-mixed gas of at full speed sending into is caught fire.
In this burner, only used the burner of diffusion flame burning to compare with the past, can reduce the growing amount of nitrogen oxide.But, in the time of further reducing the growing amount of nitrogen oxide, must make the fuel quantity of supplying with pre-mixing combustion, the fuel quantity of sending into more than carrying out the diffusion flame burning.But when increasing the amount of pre-mixed gas, it is unstable that the flame that forms in the burner becomes.Thereby the growing amount that reduces nitrogen oxide is limited.
Yet,, and can just can further suppress the generation of nitrogen oxide with the burning in the burner fully as the pre-mixed gas burning if can be with the premixed flame stabilisation.
When the burning of gas turbine burner is burnt as pre-mixed gas fully, following two problems are arranged.
(1) during low load operation, compares,, therefore become dilute combustion, be difficult to catch fire owing to sent into a large amount of combustion airs with fuel flow rate.
When (2) high capacity is turned round, owing to send into a large amount of premixed gas body and function fuel and combustion air, so the flow velocity of pre-mixed gas further increases.Thereby premixed flame becomes and is easy to be blown out.
The purpose of this invention is to provide a kind of like this gas turbine burner, it does not have the diffusion flame burning.But can make the stable burning of the rare pre-mixed gas of concentration.
The present invention is provided with main jet and chews and secondary nozzle in order to reach this purpose, makes secondary nozzle chew configuration around main jet.Main jet is chewed ejection concentration rare main pre-mixed gas, and this main pre-mixed gas contains excess air ratio greater than 1 combustion air; By secondary nozzle ejection is the secondary pre-mixed gas denseer than main pre-mixed gas.Based on this structure, form secondary flame by the dense secondary pre-mixed gas of secondary nozzle ejection, and the rare main pre-mixed gas of concentration that utilizes this secondary flame to make main jet chew ejection catches fire, thereby make the premixed flame burning.
Also have, the secondary pre-mixed gas spouting velocity that the present invention sets by secondary nozzle ejection, faster than pre-mixed gas burning velocity, but less than 2.0 meter per seconds.Like this, secondary flame is just stable.
In the present invention, secondary premixed flame is to be used to the control flame lighting main pre-mixed gas and protect main pre-mixed gas flame.As control flame optimum condition be, secondary pre-mixed gas will be with the speed ejection less than 2.0 meter per seconds, and the excess air ratio of combustion air preferably hanks 1.0 in the secondary pre-mixed gas in 0.8～1.5 scope.Like this, can suppress the generation of nitrogen oxide, and flame is blown out.
According to the present invention because the configuration mode of secondary nozzle is to chew round main jet, the secondary pre-mixed gas flame encompasses that protection flame is used the periphery of the main pre-mixed gas of ejection at full speed.Therefore protect the heat energy of the secondary pre-mixed gas flame that flame uses to pass to main pre-mixed gas flame effectively.
Chew the place ahead that sprays the pre-mixed gas direction with secondary nozzle at main jet, disposed dividing plate, and because the speed of the pre-mixed gas of two nozzles ejection has difference, so this dividing plate just makes eddy current produce.Utilize this eddy current, can promote main pre-mixed gas and secondary pre-mixed gas flame burning gas to mix, improve the ignitability of main pre-mixed gas.For example, when the thin-walled next door of use resemble the blade replaced dividing plate to separate main pre-mixed gas stream and secondary pre-mixed gas stream, because main pre-mixed gas is mobile, secondary pre-mixed gas mobile was subjected to very big influence.And under the such condition of main pre-mixed gas fray-out of flame, secondary pre-mixed gas flame has also just extinguished, and this can be confirmed by the inventor's experiment.
The present invention is, main pre-mixed gas and secondary pre-mixed gas are not near the mixing nozzle outlet, but in the formed eddy current by dividing plate, a part of main pre-mixed gas mixes mutually with a part of secondary pre-mixed gas.Thereby secondary pre-mixed gas flame is not subjected to the influence of main pre-mixed gas flame, can form long-time stable secondary premixed flame.
In the gas turbine burner of the present invention, be provided with main pre-mixed gas generating apparatus and secondary pre-mixed gas generating apparatus.This main pre-mixed gas generating apparatus to main burner air supply excess rate greater than 1.0 main pre-mixed gas.This secondary pre-mixed gas generating apparatus is to the auxiliary jet air supply excess rate secondary pre-mixed gas littler than the excess air ratio of main pre-mixed gas.Above-mentioned main pre-mixed gas generating apparatus has first air flue and first fuel passage, and this first air flue is to be communicated with the air flow circuit of being delimited by above-mentioned urceolus and above-mentioned inner core, and first fuel passage extend in first air flue.Above-mentioned secondary pre-mixed gas generating apparatus has second air flue that is communicated with above-mentioned air flow circuit, and extend into second fuel passage in this second air flue.In addition, in the gas turbine burner of the present invention, also be provided with main fuel and regulate feedway and secondary fuel supply system.This main fuel is regulated feedway, according to the load of above-mentioned steam turbine, the fuel quantity of supplying with above-mentioned main pre-mixed gas generating apparatus is regulated and is supplied with.The load of this secondary fuel supply system and above-mentioned steam turbine is irrespectively supplied with roughly a certain amount of fuel to above-mentioned secondary pre-mixed gas generating apparatus.
Below, with suitable embodiment the present invention is described.
Fig. 1 is the profilograph of the gas turbine burner of one embodiment of the invention.
Fig. 2 is the II-formed drawing in side sectional elevation of II line along Fig. 1.
Fig. 3 is the disrumpent feelings profile of the amplification of nozzle shown in Figure 1.
Fig. 4 is the performance plot of expression steam turbine load and each valve breakdown degree relation.
Fig. 5 is the performance plot that concerns between the amount of nitrogen oxide, carbon monoxide and hydrogen of the excess air ratio of the combustion air that contains in the main pre-mixed gas of expression and generation.
Fig. 6 is a component distributing performance plot in the burning gases of flame radial direction.
In Fig. 1, burner 1 is arranged to concentric shape, and urceolus 10 cylindraceous and inner core cylindraceous 20 are arranged.Between urceolus 10 and inner core 20, form the air flow circuit 30 of tubulose.By this air flow circuit 30, will import an end of inner core 20 from the gases at high pressure of compressor (not having diagram).Burn with fuel in the combustion chamber 21 that this pressure-air forms in inner core 20, be admitted to gas turbine (not having diagram) behind the formation burning gases, and in gas turbine, carry out work.
At an end of inner core 20, double-deck end wall 22,23 is being set.As clearly shown in Figure 2, at inboard end wall 22 places, have many (being 19 in the present embodiment) main jet to chew 40 on the whole circumference face, it has circular open.Secondary nozzle 50 surrounds each main jet and chews 40, and difference is opening circlewise.As Fig. 3 was shown specifically, main mouth was chewed 40 and is joined with an end of the main premixed tube 41 that passes end wall 23 back, the outside and stretch out.The other end of main premixed tube 41 is towards air chamber 31 openings that are connected with air flow circuit 30.In each main premixed tube 41, stretch into fuel-supply pipe 60.Fuel-supply pipe 60 is from being equipped with delivery of main fuel pipe 62 branches (Fig. 1) of fuel control valve 61.From the fuel of the end of fuel-supply pipe 60 ejection, be pre-mixed in main premixed tube 41 with air from air chamber 31, generate main pre-mixed gas.On each fuel-supply pipe 60, choke valve 63 is housed.
As shown in Figure 3, secondary nozzle 50 joins with an end of tube 51.Tube 51 extend in the secondary premixing cavity 52 that forms between the end walls 22,23.
As shown in Figure 1, by the fuel-supply pipe 54 that fuel control valve 53 is housed, can in secondary premixing cavity 52, send into fuel.The fuel of being sent into by fuel-supply pipe 54 is pre-mixed with the air that is imported by several airports 24 in secondary premixing cavity 52, generate secondary pre-mixed gas, and airport 24 is formed on the inner peripheral portion of inner core 20 between the end walls 22,23.
Controller 70(Fig. 1) reads the load and the velocity of rotation of gas turbine.Controller 70 sends instruction according to load and velocity of rotation to valve 61,63, controls, and choke valve 63 is normally close valves, when receiving the open command signal of controller 70, and its just complete breakdown.
As shown in Figure 4, along with the increase of steam turbine load, choke valve 63 is breakdown one by one just.In addition, the breakdown degree of fuel control valve 61 roughly is proportional to the load of steam turbine and increases, and the load of the opening degree of fuel control valve 53 and steam turbine is irrelevant, roughly is certain (about 10%).Like this, in secondary premixing cavity 52, roughly be that a certain amount of fuel and combustion air carry out premixed.In contrast, change, the excess air ratio of the combustion air in the main premixed tube 41 is remained on more than 1 owing to the opening degree of fuel control valve 53 is based on steam turbine load.
And the present invention sets the aperture area of secondary nozzle 50 like this, makes by the secondary pre-mixed gas spouting velocity of secondary nozzle 50 ejections identical with flame combustion speed (0.5 meter per second).In contrast, main jet is chewed 40 and is had big aperture area, makes it to spray main pre-mixed gas with higher speed (more than 20 meter per seconds).
The following describes the work of this burner.
At first, open fuel control valve 53, fuel is imported secondary premixing cavity 52, form secondary pre-mixed gas.Then, by spark plug (not having diagram) the secondary pre-mixed gas of secondary nozzle 50 ejections is lighted a fire.The excess air ratio of combustion air is set near 1 in the secondary pre-mixed gas, is preferably 1.0.In addition, as previously mentioned, the spouting velocity of secondary pre-mixed gas is controlled in below 2.0 meter per seconds.Thereby catching fire of secondary pre-mixed gas had assurance, and can obtain stable flame combustion.
At this moment, because nearly all choke valve 63 is cutting out, spray combustion airs so chew 40 from main jet.Controller 70 reads the change conditions of gas turbine load, and sends instruction to fuel control valve 61, makes it to increase the degree of unlatching.When the opening degree of fuel control valve 61 slowly increased, choke valve 63 was also just opened along with the increase of opening degree in turn.Thereby, in main premixed tube 41, form main pre-mixed gas, and chew 40 by main jet and in combustion chamber 21, at full speed spray main pre-mixed gas.Chew the main pre-mixed gas of 40 ejections by main jet, lighted, form main pre-mixed gas flame 42(Fig. 3) by the secondary pre-mixed gas flame 55 that around it, forms.
Along with choke valve 63 is opened successively, the main jet that forms main premixed flame 42 is chewed 40 number to be increased gradually.Then, at gas turbine load during, chew at all main jets and to have formed main pre-mixed gas flame 42 on 40 for rated value.
Usually, for the generating gas turbine, to 100% load, the velocity of rotation of gas turbine is certain from 0% load.And the air capacity of being supplied with to burner by gas turbine powered compressor roughly is certain.Therefore, by air flow circuit 30, air chamber 31, the amount that imports to the combustion air of main premixed tube 41 also roughly is certain.
As previously mentioned, the fuel quantity by fuel control valve 61 is supplied with increases pro rata with steam turbine load.But owing to also increased pro rata with steam turbine load by the number of the choke valve 63 of breakdown, therefore, the fuel quantity that the choke valve 63 of each breakdown is sent into toward main premixed tube 41 roughly is certain.So in main premixed tube 41, the excess air ratio of combustion air does not have big variation in the main pre-mixed gas of formation.Therefore, in the present embodiment, main pre-mixed gas is the rare gas of concentration, and the excess air ratio of combustion air is set in more than 1 in the promptly main pre-mixed gas, preferably is set in about 1.5.
In the present embodiment, owing to be set near 1 by the excess air ratio of combustion air in the secondary pre-mixed gas of secondary nozzle 50 ejections, so flame combustion is stable, has the characteristic of good protection flame.So even chew the 40 high-speed main pre-mixed gas that spray dilute concentrations from main jet, the combustion flame of secondary pre-mixed gas can not blown out yet, and also can guarantee to light main pre-mixed gas.
Shown in Figure 5 is, during the excess air ratio of combustion air, nitrogen oxide, hydrogen and carbon monoxide be the variation of growing amount separately in changing main pre-mixed gas.As shown in this embodiment, when the excess air ratio of combustion air in the main pre-mixed gas 1.5 when above, shown in solid line, the growing amount of nitrogen oxide significantly reduces.Shown in chain-dotted line and double dot dash line, hydrogen and carbon monoxide growing amount separately is roughly zero.Certainly, the generation of oxygen is shown in dotted line has increased.
Because the excess air ratio of combustion air approaches 1 in the secondary pre-mixed gas, so the growing amount of nitrogen oxide is just many in the secondary pre-mixed gas.Yet, when the load of steam turbine is rated value, deliver to fuel quantity in the secondary pre-mixed gas only for delivering to about 10% of whole fuel quantities in the burner.So for the whole burning gases from burner, the growing amount of nitrogen oxide is still few.
Shown in Figure 6 is, is positioned at from main jet to chew burning gases component distributing on the outside radial direction in 40 center.Result among the figure obtains like this: the position from main jet is chewed 5 millimeters of the main pre-mixed gas direction downstream sides of 40 ejections, and the sample detecting device is set, and outwards moves, thereby gather burning gases at radial direction, analyze.Conclusively show among the figure, in the inboard of main pre-mixed gas flame, hydrocarbon is residual as unburned composition.But promptly outside more along radial direction the closer to secondary premixed flame, hydrocarbon has just burnt gradually, and in the position of secondary nozzle, hydrocarbon all burns.Therefore, can know and find out that burning is to shift to main pre-mixed gas flame from secondary pre-mixed gas flame really.
Claims (9)
1, a kind of gas turbine burner, this burner comprises: urceolus; Be arranged on the inside of above-mentioned urceolus, and form the inner core of combustion chamber in the inboard; Be arranged on the main burner on the end wall of above-mentioned inner core; Auxiliary jet round above-mentioned main burner setting; It is characterized in that main pre-mixed gas generating apparatus: to above-mentioned main burner air supply excess rate greater than 1 main pre-mixed gas; Secondary pre-mixed gas generating apparatus: supply with secondary pre-mixed gas to above-mentioned auxiliary jet, the excess air ratio of this pair pre-mixed gas is littler than the excess air ratio of above-mentioned main pre-mixed gas.
2, gas turbine burner according to claim 1, it is characterized in that: above-mentioned main pre-mixed gas generating apparatus has first air flue and first fuel passage, above-mentioned first air flue is to be communicated with the air flow circuit of being delimited by above-mentioned urceolus and above-mentioned inner core, and first fuel passage extend in first air flue; Above-mentioned secondary pre-mixed gas generating apparatus has second air flue that is communicated with above-mentioned air flow circuit, and extend into second fuel passage in this second air flue.
3, gas turbine burner according to claim 1, it is characterized in that: the excess air ratio of above-mentioned main pre-mixed gas is gone into greater than 1.0 and less than 1.5(1.0≤go into≤1.5), the excess air ratio of above-mentioned secondary pre-mixed gas is gone into greater than 0.8 and less than 1.5(0.8≤go into≤1.5).
4, gas turbine burner according to claim 1 is characterized in that: above-mentioned secondary pre-mixed gas is faster than the burning velocity of this pair pre-mixed gas from the speed V of above-mentioned auxiliary jet ejection.And below 2.0 meter per seconds (V≤2.0m/s).
5, gas turbine burner according to claim 1 is characterized in that, also comprises: according to the load of above-mentioned steam turbine, will supply with the main fuel adjusting feedway that above-mentioned main pre-mixed gas generating apparatus fuel quantity is regulated and supplied with; Irrespectively supply with the secondary fuel supply system of a certain amount of fuel with the load of above-mentioned steam turbine to above-mentioned secondary pre-mixed gas generating apparatus.
6, gas turbine burner according to claim 5 is characterized in that: from the speed of the main pre-mixed gas of above-mentioned main burner ejection more than 20 meter per seconds; And from the speed of the above-mentioned secondary pre-mixed gas of above-mentioned auxiliary jet ejection below 2.0 meter per seconds.
7, gas turbine burner according to claim 5 is characterized in that: the excess air ratio of above-mentioned secondary pre-mixed gas is 0.8～1.5(0.8≤excess air ratio≤1.5).
8, gas turbine burner according to claim 5 is characterized in that: the opening shape of above-mentioned auxiliary jet is the ring-type concentric with the opening of above-mentioned main burner.
9, gas turbine burner according to claim 5 is characterized in that: above-mentioned main burner and auxiliary jet are at same plane inner opening.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP880206/87 | 1987-09-04 | ||
| JP880206 | 1987-09-04 | ||
| JP62220206A JP2528894B2 (en) | 1987-09-04 | 1987-09-04 | Gas turbine combustor |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN1032230A CN1032230A (en) | 1989-04-05 |
| CN1011064B true CN1011064B (en) | 1991-01-02 |
Family
ID=16747549
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 88106413 Expired CN1011064B (en) | 1987-09-04 | 1988-09-03 | Gas turbine combustor |
Country Status (5)
| Country | Link |
|---|---|
| EP (1) | EP0335978B1 (en) |
| JP (1) | JP2528894B2 (en) |
| CN (1) | CN1011064B (en) |
| DE (1) | DE3854666T2 (en) |
| WO (1) | WO1989002052A1 (en) |
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| DE1074920B (en) * | 1955-07-07 | 1960-02-04 | Ing habil Fritz A F Schmidt Murnau Dr (Obb) | Method and device for regulating gas turbine combustion chambers with subdivided combustion and several pressure levels |
| CH407653A (en) * | 1962-07-24 | 1966-02-15 | Prvni Brnenska Strojirna | Burners for gaseous and liquid fuel, in particular for gas turbines |
| US3919840A (en) | 1973-04-18 | 1975-11-18 | United Technologies Corp | Combustion chamber for dissimilar fluids in swirling flow relationship |
| US4100733A (en) * | 1976-10-04 | 1978-07-18 | United Technologies Corporation | Premix combustor |
| JPS5857656A (en) * | 1981-09-30 | 1983-04-05 | Toshiba Corp | Switching device of control loop |
| DE3361535D1 (en) * | 1982-05-28 | 1986-01-30 | Bbc Brown Boveri & Cie | Gas turbine combustion chamber and method of operating it |
| JPS6057131A (en) * | 1983-09-08 | 1985-04-02 | Hitachi Ltd | Fuel feeding process for gas turbine combustor |
| EP0169431B1 (en) * | 1984-07-10 | 1990-04-11 | Hitachi, Ltd. | Gas turbine combustor |
| JPH0630589Y2 (en) * | 1989-04-19 | 1994-08-17 | 石川島播磨重工業株式会社 | Supporting device for suspension frame in traveling carriage |
-
1987
- 1987-09-04 JP JP62220206A patent/JP2528894B2/en not_active Expired - Fee Related
-
1988
- 1988-08-31 DE DE3854666T patent/DE3854666T2/en not_active Expired - Fee Related
- 1988-08-31 EP EP88907798A patent/EP0335978B1/en not_active Expired - Lifetime
- 1988-08-31 WO PCT/JP1988/000870 patent/WO1989002052A1/en active IP Right Grant
- 1988-09-03 CN CN 88106413 patent/CN1011064B/en not_active Expired
Also Published As
| Publication number | Publication date |
|---|---|
| EP0335978A1 (en) | 1989-10-11 |
| CN1032230A (en) | 1989-04-05 |
| EP0335978B1 (en) | 1995-11-08 |
| WO1989002052A1 (en) | 1989-03-09 |
| EP0335978A4 (en) | 1989-12-13 |
| JP2528894B2 (en) | 1996-08-28 |
| JPS6463721A (en) | 1989-03-09 |
| DE3854666D1 (en) | 1995-12-14 |
| DE3854666T2 (en) | 1996-04-25 |
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