CN203879631U - Ground-based combustion gas turbine using pulse detonation combustion - Google Patents
Ground-based combustion gas turbine using pulse detonation combustion Download PDFInfo
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- CN203879631U CN203879631U CN201420294056.8U CN201420294056U CN203879631U CN 203879631 U CN203879631 U CN 203879631U CN 201420294056 U CN201420294056 U CN 201420294056U CN 203879631 U CN203879631 U CN 203879631U
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Abstract
The utility model discloses a ground-based combustion gas turbine using pulse detonation combustion. The combustion gas turbine comprises a gas compressor, a gas storage chamber, a plurality of gas supply pipelines, a plurality of pulse detonation combustion chambers, a pressure shaping chamber, a turbine, a rotor and a tail jet pipe, wherein the gas compressor is mounted at the forefront end of the ground-based combustion gas turbine, a gas outlet end of the gas compressor is sequentially connected to the gas storage chamber, the pressure shaping chamber, the turbine and the tail jet pipe, the rotor is arranged in the center of the gas compressor and turbine and is respectively connected with the gas compressor and turbine by virtue of the two bearings, one end of the rotor is led out from the tail jet pipe; a plurality of pulse detonation combustion chambers are arranged at the circumferential direction of the gas storage chamber and pressure shaping chamber, an outlet of the gas storage chamber is respectively connected with inlets of a plurality of pulse detonation combustion chambers by virtue of a plurality of gas supply pipelines, outlets of a plurality of pulse detonation combustion chambers are respectively connected to the inlet of the pressure shaping chamber and a spark plug and a fuel pipeline are arranged at the circumference of a single pulse detonation combustion chamber. During the use, a leading-out end of the rotor is connected to a generator assembly by virtue of a transmission.
Description
[technical field]
The utility model relates to a kind of gas turbine, particularly a kind of ground gas turbine that utilizes pulse detonation combustion.
[background technique]
Ground gas turbine all adopts the mode of isobaric combustion to discharge fuel heat, isobaric combustion is a kind of deflagration burning, and its velocity of propagation of flame is lower, is generally about several meters to tens metre per second (m/s)s, and gas compressor in gas turbine exit velocity is higher, flame combustion chamber is very easily blown out.Reliable and stable for ensureing flame combustion chamber, generally need the structure of well-designed firing chamber, adopt the flame holders such as cyclone separator, cavity, THE BARCHAN DUNE VORTEX, form low speed whirlpool district at head of combustion chamber, make part fire high-temperature combustion product and produce the motion that refluxes, formation has the constant ignition source of auto-compensation ability, constantly to light the fresh not ignition mixture of combustion, thereby reaches the object of the steady flame.But along with market is to the regulation of ground gas turbine pollutant emission index and require increasingly stringent, design cost and the technical difficulty of gas-turbine combustion chamber constantly increase, and advanced low pollution combustor all adopts lean fuel premixed combustion mode at present.Because firing chamber fuel is always in lean burn condition, therefore firing chamber is more easily put out by high velocity air, cause the combustion stability region of firing chamber to narrow.
In order to ensure gas turbine stable operation for a long time, situation about narrowing for combustion chambers burn stability region, must design extremely complicated firing chamber control system, and control accuracy and control system reaction velocity have been proposed to strict requirement.In the time that the situations such as gas turbine component upgrading, parts dismounting installation or replacing, component inspection, propellant composition variation occur, the stability region of gas-turbine combustion chamber all will change, now also need gas turbine to carry out complicated combustion adjustment test, to guarantee that firing chamber is operated in the intermediate value in flameholding region, burning adjustment and the control technique of firing chamber therefore the safety and reliability of gas turbine places one's entire reliance upon.
Mainly there are the following problems: 1, chamber structure complexity for gas turbine based on isobaric combustion at present; 2, chamber coolant system complexity, needs large quantity of air to carry out it cooling, and the AIR Proportional of actual participation burning is little; 3, combustion chambers burn region of stability is narrow, easily flame-out, needs complicated flame stabilization structure smooth combustion chamber flame; 4, firing chamber control system complexity; 5, need frequently carry out combustion adjustment test; 6, the raising of gas turbine heating power circulation overall performance is subject to the restriction of turbine exotic material.
[model utility content]
AIR Proportional that the purpose of this utility model is to solve the existing chamber structure complexity of existing ground gas turbine, actual participation burning is little, flameholding region is narrow, easy flame-out and problems such as adjustment of need frequently burning, a kind of ground gas turbine that utilizes pulse detonation combustion is proposed, its chamber structure adopting is simple, without cooling air membrane pore structure, do not need complicated flame holder; Firing chamber does not need cooling-air, and pressurized air can all participate in burning; With Supersonic transport, there is not combustion stability and flame-out problem in flame combustion chamber, and does not need firing chamber to carry out combustion adjustment test, and burning pollutant discharge is simultaneously low; In addition combustion process has from supercharging feature, therefore can reduce gas compressor progression, reduces power input to compressor, increases generated energy, improves thermal efficiency of cycle.
For achieving the above object, the utility model adopts following technological scheme:
Utilize a ground gas turbine for pulse detonation combustion, comprise gas compressor, gas storage chamber, multiple supply air line, multiple pulse detonation combustor, pressure shaping chamber, turbine, rotor and jet pipe; Wherein, gas compressor is arranged at this ground gas turbine foremost, the outlet side of gas compressor is connected with jet pipe with gas storage chamber, pressure shaping chamber, turbine successively, rotor is arranged at the center of gas compressor and turbine, and be connected with turbine with gas compressor respectively by two bearings, draw from jet pipe one end of rotor; Multiple pulse detonation combustors are arranged between gas storage chamber and pressure shaping chamber, and be evenly arranged ringwise centered by rotor, the outlet of gas storage chamber is connected with the entrance of multiple pulse detonation combustors by supply air line respectively, the outlet of multiple pulse detonation combustors is connected with the entrance of pressure shaping chamber respectively, individual pulse detonation combustor be circumferentially with spark plug and fuel conduit.
The utility model further improves and is: multiple pulse detonation combustors are circular pipe type tilting and are arranged on the periphery of gas turbine gas storage chamber, pulse detonation combustor is uniform section throat less chamber, comprises the head of combustion chamber end cap, firing chamber igniting section, the firing chamber section of detonating, firing chamber pinking section and the firing chamber changeover portion that connect successively; Wherein, head of combustion chamber end cap is provided with main nozzle, main nozzle is provided with main nozzle gas circuit and main nozzle fuel conduit, the firing chamber section of detonating and firing chamber pinking section be circumferentially with 3～8 equally spaced pilot jets, pilot jet is provided with pilot jet gas circuit and pilot jet fuel conduit; Spark plug is arranged on the circumferential of firing chamber igniting section, supply air line is connected with main nozzle gas circuit and 3～8 pilot jet gas circuits respectively by the air distributor that is arranged on its outlet end, and on the pipeline being connected with some pilot jet gas circuits respectively at air distributor, be equipped with pilot jet air switching sol, the entrance of the outlet Bonding pressure shaping chamber of firing chamber changeover portion.
The utility model further improves and is: firing chamber pinking section inner side be circumferentially provided with spirality enhanced detonation structure.
The utility model further improves and is: the Outlet of rotor is connected with generator assembly by speed changer.
The utility model further improves and is: on multiple supply air lines, be equipped with air flow rate adjustment valve and Air flow meter.
The utility model further improves and is: jet pipe is an elbow bend jet pipe.
The utility model further improves and is: the end of gas storage chamber is provided with venting bypass, and venting bypass is provided with the high-frequency electromagnetic valve for controlling venting by-pass switch.
The utility model further improves and is: the entrance of gas storage chamber is expanssion type annular pass, and the main body of gas storage chamber is prismatic annular housing.
The utility model further improves and is: pressure shaping chamber comprises casing I, and the toroidal membrane I being differed by multiple length in casing I inside is divided into multiple annular passs, and multiple annular pass is strengthened by criss-cross bulkhead bracket I.
The utility model further improves and is: pressure shaping chamber comprises casing II, and the toroidal membrane II that casing II inside is equated by multiple axial length is divided into multiple expansions or convergent contour annular pass, and multiple annular pass is strengthened by criss-cross bulkhead bracket II.
With respect to prior art, the utlity model has following technique effect:
The utility model is compared with traditional ground gas turbine, because pulse detonation combustion has from supercharging, flame propagation speed (generally 10
3m/s magnitude), the advantage such as combustion efficiency is high, pollutant emission is low, therefore the utility model adopts pulse detonation combustor to replace after traditional constant-pressure combustion chamber, gas turbine can reduce gas compressor progression greatly, reduce gas compressor compression work, and then make to increase for the ratio of generating electricity in turbine output shaft power, improve on the whole the thermal efficiency of cycle of gas turbine;
Because pulse detonation combustion velocity of propagation is 10
3m/s magnitude, ignition mixture moment burning heat release under the effect of knocking combustion ripple in firing chamber, combustion efficiency is high and do not have combustion stability and easy flame-out problem, adopts combustion with reduced pollutants technology after-burner flameholding region to narrow and the easy problem such as flame-out therefore the utility model can successfully solve in conventional gas turbine;
Because pulse detonation combustion does not exist flameholding and flame-out problem, therefore the utility model can significantly reduce the combustion control system of firing chamber, and can save and in conventional gas turbine, need the test procedure of frequently burning and adjusting; Pulse detonation combustion is a kind of homogeneous phase premixed combustion simultaneously, and its velocity of combustion is very fast, and products of combustion is very short in the waiting time of high-temperature zone, can greatly reduce the discharge of the pollutant such as NOx, CO; In addition because pulse detonation combustion has periodic intermittence, the not severe working environment in high temperature, high-pressure gas always of firing chamber and turbine blade, therefore its material and cooling technology to firing chamber requires lower, compared with existing gas turbine, after employing pulse detonation combustion no longer there is temperature limited problem in firing chamber and the turbine blade of gas turbine.
[brief description of the drawings]
Fig. 1 is the overall pie graph of a kind of ground gas turbine that utilizes pulse detonation combustion of the utility model;
Fig. 2 is the diagrammatic sectional view of the firing chamber of the utility model ground gas turbine;
Fig. 3 is the structure diagram of pressure shaping chamber first scheme of the utility model ground gas turbine;
Fig. 4 is that the A-A of Fig. 3 is to view;
Fig. 5 is the structure diagram of the pressure shaping chamber alternative plan of the utility model ground gas turbine;
Fig. 6 is that the B-B of Fig. 5 is to view.
Wherein: 1, gas compressor; 2, gas storage chamber; 3, supply air line; 4, air flow rate adjustment valve; 5, air distributor; 6, pilot jet air switching sol; 7, pulse detonation combustor; 8, pressure shaping chamber; 9, turbine; 10, rotor; 11, speed changer; 12, generator assembly; 13, jet pipe; 14, venting bypass; 15, Air flow meter; 16, bearing; 17, venting by-pass switch solenoid valve; 18, combustion gas stream; 19, main nozzle gas circuit; 20, main nozzle; 21, main nozzle fuel conduit; 22, spark plug; 23, pilot jet; 24, pilot jet gas circuit; 25, pilot jet fuel conduit; 26, spirality enhanced detonation structure; 27, firing chamber changeover portion; 28, firing chamber pinking section; 29, the firing chamber section of detonating; 30, firing chamber igniting section; 31, head of combustion chamber end cap; 32, bulkhead bracket I; 33, toroidal membrane I; 34, casing I; 35, bulkhead bracket II; 36, toroidal membrane II; 37, casing II.
[embodiment]
Below in conjunction with accompanying drawing, the utility model is described in further detail.
Referring to Fig. 1, a kind of ground gas turbine that utilizes pulse detonation combustion of the utility model, comprise gas compressor 1, gas storage chamber 2, multiple supply air line 3, multiple pulse detonation combustor 7, pressure shaping chamber 8, turbine 9, rotor 10 and jet pipe 13, and the stream of their combustion gas, i.e. combustion gas stream 18 are passed through in formation as shown by the arrows in Figure 1.
Wherein, gas compressor 1 is arranged at this ground gas turbine foremost, the outlet side of gas compressor 1 is connected with gas storage chamber 2, pressure shaping chamber 8, turbine 9 and jet pipe 13 successively, rotor 10 is arranged at the center of gas compressor 1 and turbine 9, and be connected with turbine 9 with gas compressor 1 respectively by two bearings 16, draw from jet pipe 13 one end of rotor 10; Multiple pulse detonation combustors 7 are arranged between gas storage chamber 2 and pressure shaping chamber 8, and be evenly arranged ringwise centered by rotor (10), the outlet of gas storage chamber 2 is connected with the entrance of multiple pulse detonation combustors 7 by supply air line 3 respectively, the outlet of multiple pulse detonation combustors 7 is connected with the entrance of pressure shaping chamber 8 respectively, individual pulse detonation combustor 7 be circumferentially with spark plug 22 and fuel conduit.When use, the Outlet of rotor 10 is connected with generator assembly 12 by speed changer 11.
Referring to Fig. 2, multiple pulse detonation combustors 7 are circular pipe type tilting and are arranged on the periphery of gas turbine gas storage chamber 2, wherein, pulse detonation combustor 7 is uniform section throat less chamber, comprise the head of combustion chamber end cap 31, firing chamber igniting section 30, the firing chamber section of detonating 29, firing chamber pinking section 28 and the firing chamber changeover portion 27 that connect successively, it is for being transitioned into gradually the bending component of sector crosssection from circle, wherein, head of combustion chamber end cap 31 is provided with main nozzle 20, main nozzle 20 is provided with main nozzle gas circuit 19 and main nozzle fuel conduit 21, the firing chamber section of detonating 29 and firing chamber pinking section 28 be circumferentially with 3～8 equally spaced pilot jets 23, this can reduce the filling time of pulse detonation combustor 7, improve the frequency of okperation of pulse detonation combustor 7, pilot jet 23 is provided with pilot jet gas circuit 24 and pilot jet fuel conduit 25, firing chamber pinking section 28 inner sides be circumferentially provided with spirality enhanced detonation structure 26, spark plug 22 is arranged on the circumferential of firing chamber igniting section 30, supply air line 3 is connected with main nozzle gas circuit 19 and some pilot jet gas circuits 24 respectively by the air distributor that is arranged on its outlet end, and be equipped with pilot jet air switching sol 6 on the pipeline being connected with some pilot jet gas circuits 24 respectively at air distributor, control the fuel of each pilot jet 23 supplies with by pilot jet air switching sol 6, and main nozzle 20 is directly connected with air distributor 5, be that main nozzle 20 is always in open-circuit condition, but because knocking combustion has from pressurization, when after the interior generation detonation wave of pulse detonation combustor 7, pulse detonation combustor 7 internal pressures raise suddenly, pulse detonation combustor 7 pressure are greater than main nozzle 20 exit flow pressure, cause main nozzle 20 fuel under the effect of pressure difference, automatically to stop supplying with, and when after detonation wave discharge pulse detonation combustor 7, pulse detonation combustor 7 pressure decline rapidly, pressure difference reduces to 0 or less, main nozzle 20 can recover again fuel supply automatically, be that main nozzle 20 always works in self adaption fuel supply model, the entrance of the outlet Bonding pressure shaping chamber 8 of firing chamber changeover portion 27.
Further, supply air line 3 is metal circular tube, on multiple supply air lines 3, be equipped with air flow rate adjustment valve 4 and Air flow meter 15, can accurately control air mass flow size, to meet the air mass flow requirement of the various mode of operations of gas turbine under different load.Jet pipe 13 is an elbow bend jet pipe, fuel gas flow direction can be changed to 90 degree.
Further, the entrance of gas storage chamber 2 is expanssion type annular pass, gas compressor 1 exports the subsonic flow supercharging of slowing down behind expanssion type annular pass, the main body of gas storage chamber 2 is a prismatic annular housing, its end is provided with venting bypass 14, and venting bypass 14 is provided with the high-frequency electromagnetic valve 17 for controlling venting bypass 14 switches.Control the switch of venting bypass by high-frequency electromagnetic valve 17, in the time that pulse detonation combustor 7 produces detonation wave, can unnecessary pressurized air be directly expelled to combustor exit by venting bypass 14.
Pressure shaping chamber 8 is positioned at the downstream of pulse detonation combustor 7, the Main Function of pressure shaping chamber 8 is that paired pulses detonation pressure ripple carries out shaping, reduce, the pressure pulsation of mild pulse-knocking combustion gas, can reduce the pressure surge of pulse-knocking combustion gas by pressure shaping chamber 8, be beneficial to the energy extraction of turbine 9 to pinking combustion gas.
For this reason, the utility model provides two kinds of pressure shaping chamber schemes, Fig. 3 is the structure diagram of pressure shaping chamber the first scheme, uniform section toroidal membrane I 33 and bulkhead bracket I 32 that it is mainly differed by length form, pressure shaping chamber 8 is divided into four annular passs that clapboard spacing is increased gradually by skin to internal layer by shellring shape dividing plate I 33, due to the effect of air-flow viscous force, the combustion gas of discharging from pulse detonation combustor 7 changeover portions is the fastest at the mean velocity of the passage of the first scheme pressure shaping chamber 8 internal partition spacing maximums, and it is minimum at the passage combustion gas mean velocity of distance between partitions minimum, therefore behind the first scheme pressure shaping chamber 8, single flash detonation pressure ripple has been broken down into the pressure wave on four times with precedence.
Fig. 4 is the structure diagram of pressure shaping chamber alternative plan, variable cross section toroidal membrane II 36 and bulkhead bracket II 35 that it is mainly equated by axial length form, pressure shaping chamber 8 is divided into four expansions or convergent contour variable cross section annular pass by shellring shape dividing plate II 36, because supersonic flow is speedup step-down at expansion shape passage, deceleration supercharging at convergent contour passage, the ultrasound velocity combustion gas of therefore discharging from pulse detonation combustor changeover portion is behind alternative plan pressure shaping chamber 8, single flash detonation pressure ripple also can be broken down into the pressure wave on four times with precedence, play the effect of the mild shaping of pressure.
In addition, because knocking combustion has from supercharging advantage, gas compressor 1 is identical with conventional gas turbine gas compressor, but progression is reduced to 2 to 3 grades.Turbine 9 is identical with conventional gas turbine turbine.Speed changer and generator assembly that speed changer 11 adopts with conventional gas turbine with generator assembly 12 are identical.
For model utility is further understood, now its working procedure is done to an explanation.
When a kind of ground gas turbine work that utilizes pulse detonation combustion of the utility model, ambient air is sucked gas turbine by gas compressor 1, and after compressed supercharging, enter gas storage chamber 2, by supply air line 3 and by air distributor 5 by pressurized air be divided into multiply air-flow together with fuel through firing chamber main nozzle 20 and multichannel pilot jet 23 filler pulse detonation combustors, after end to be filled, light a fire and form knocking combustion ripple by detonation chamber head breeze plug 22, knocking combustion ripple is with Supersonic transport combustion fuel heat release, at a high speed, high temperature pulse pinking combustion gas is behind pressure shaping chamber 8, expand and do work by turbine 9, the weary gas having expanded is finally discharged through jet pipe 13, turbine merit with the formal output of air horsepower to gas compressor 1 and generator assembly 12, between rotor 10 and generator assembly 12, be connected by speed changer 11.
Further specifically, utilize starting source of the gas filler pulse detonation combustor, sending ignition order by control system lights a fire by spark plug 22, control system is given an order and is closed pilot jet air switching sol 6 simultaneously, detonation chamber enters pressure shaping chamber 8 through firing chamber changeover portion 27 after forming detonation wave, pinking combustion gas enters at a high speed the interior expansion acting of turbine 9 after shaping, turbine 9 with the formal output power of air horsepower to gas compressor 1 and generator 12, the weary gas of low speed expanding after acting is discharged through jet pipe 13, gas compressor 1 sucks and compresses external environment air, air after compression flows into gas storage chamber 2 through expansion shape passage deceleration supercharging, then supply with each pulse detonation combustor 7 through supply air line 3 and air distributor 5, when detonation wave spreads out of behind firing chamber, each pilot jet air switching sol 6 is opened, main nozzle 20 and pilot jet 23 are filled firing chamber simultaneously, after spark plug 22 igniting, each pilot jet air switching sol 6 is closed again, so circulation, in this process, in the time that gas storage chamber 2 pressure reach blow off pressure, venting by-pass switch solenoid valve 17 is opened, pressurized air is directly expelled to firing chamber changeover portion 27 by venting bypass.
Claims (10)
1. a ground gas turbine that utilizes pulse detonation combustion, is characterized in that: comprise gas compressor (1), gas storage chamber (2), multiple supply air line (3), multiple pulse detonation combustor (7), pressure shaping chamber (8), turbine (9), rotor (10) and jet pipe (13); Wherein, gas compressor (1) is arranged at this ground gas turbine foremost, the outlet side of gas compressor (1) is connected with gas storage chamber (2), pressure shaping chamber (8), turbine (9) and jet pipe (13) successively, rotor (10) is arranged at the center of gas compressor (1) and turbine (9), and be connected with turbine (9) with gas compressor (1) respectively by two bearings (16), draw from jet pipe (13) one end of rotor (10); Multiple pulse detonation combustors (7) are arranged between gas storage chamber (2) and pressure shaping chamber (8), and be evenly arranged ringwise centered by rotor (10), the outlet of gas storage chamber (2) is connected with the entrance of multiple pulse detonation combustors (7) by supply air line (3) respectively, the outlet of multiple pulse detonation combustors (7) is connected with the entrance of pressure shaping chamber (8) respectively, individual pulse detonation combustor (7) be circumferentially with spark plug (22) and fuel conduit.
2. a kind of ground gas turbine that utilizes pulse detonation combustion according to claim 1, it is characterized in that: multiple pulse detonation combustors (7) are circular pipe type tilting and are arranged on the periphery of gas turbine gas storage chamber (2), pulse detonation combustor (7) is uniform section throat less chamber, comprises the head of combustion chamber end cap (31), firing chamber igniting section (30), the firing chamber section of detonating (29), firing chamber pinking section (28) and the firing chamber changeover portion (27) that connect successively; Wherein, head of combustion chamber end cap (31) is provided with main nozzle (20), main nozzle (20) is provided with main nozzle gas circuit (19) and main nozzle fuel conduit (21), the firing chamber section of detonating (29) and firing chamber pinking section (28) be circumferentially with 3～8 equally spaced pilot jets (23), pilot jet (23) is provided with pilot jet gas circuit (24) and pilot jet fuel conduit (25); Spark plug (22) is arranged on the circumferential of firing chamber igniting section (30), supply air line (3) is connected with main nozzle gas circuit (19) and 3～8 pilot jet gas circuits (24) respectively by the air distributor that is arranged on its outlet end, and on the pipeline being connected with some pilot jet gas circuits (24) respectively at air distributor, be equipped with pilot jet air switching sol (6), the entrance of the outlet Bonding pressure shaping chamber (8) of firing chamber changeover portion (27).
3. a kind of ground gas turbine that utilizes pulse detonation combustion according to claim 2, is characterized in that: firing chamber pinking section (28) inner side be circumferentially provided with spirality enhanced detonation structure (26).
4. according to a kind of ground gas turbine that utilizes pulse detonation combustion described in any one in claims 1 to 3, it is characterized in that: the Outlet of rotor (10) is connected with generator assembly (12) by speed changer (11).
5. according to a kind of ground gas turbine that utilizes pulse detonation combustion described in any one in claims 1 to 3, it is characterized in that: on multiple supply air lines (3), be equipped with air flow rate adjustment valve (4) and Air flow meter (15).
6. according to a kind of ground gas turbine that utilizes pulse detonation combustion described in any one in claims 1 to 3, it is characterized in that: jet pipe (13) is an elbow bend jet pipe.
7. according to a kind of ground gas turbine that utilizes pulse detonation combustion described in any one in claims 1 to 3, it is characterized in that: the end of gas storage chamber (2) is provided with venting bypass (14), and venting bypass (14) is provided with the high-frequency electromagnetic valve (17) for controlling venting bypass (14) switch.
8. according to a kind of ground gas turbine that utilizes pulse detonation combustion described in any one in claims 1 to 3, it is characterized in that: the entrance of gas storage chamber (2) is expanssion type annular pass, the main body of gas storage chamber (2) is prismatic annular housing.
9. according to a kind of ground gas turbine that utilizes pulse detonation combustion described in any one in claims 1 to 3, it is characterized in that: pressure shaping chamber (8) comprise casing I (34), the inner toroidal membrane I (33) being differed by multiple length of casing I (34) is divided into multiple annular passs, and multiple annular pass is strengthened by criss-cross bulkhead bracket I (32).
10. according to a kind of ground gas turbine that utilizes pulse detonation combustion described in any one in claims 1 to 3, it is characterized in that: pressure shaping chamber (8) comprise casing II (37), the inner toroidal membrane II (36) being equated by multiple axial length of casing II (37) is divided into multiple expansions or convergent contour annular pass, and multiple annular pass is strengthened by criss-cross bulkhead bracket II (35).
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| Application Number | Priority Date | Filing Date | Title |
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| CN201420294056.8U CN203879631U (en) | 2014-06-04 | 2014-06-04 | Ground-based combustion gas turbine using pulse detonation combustion |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201420294056.8U CN203879631U (en) | 2014-06-04 | 2014-06-04 | Ground-based combustion gas turbine using pulse detonation combustion |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN104033248A (en) * | 2014-06-04 | 2014-09-10 | 华能国际电力股份有限公司 | Ground gas turbine using pulse knocking combustion |
| CN107250509A (en) * | 2015-02-17 | 2017-10-13 | 赛峰直升机发动机 | Isochoric combustion system for the turbogenerator of aircraft engine |
| CN107781847A (en) * | 2017-09-22 | 2018-03-09 | 中国华能集团公司 | The burner of double gaseous fuels and the gas turbine operation method using the burner |
| CN109154441A (en) * | 2016-05-23 | 2019-01-04 | 赛峰集团 | Toroidal combustion chamber with continuous detonation wave |
| CN110057487A (en) * | 2019-04-19 | 2019-07-26 | 中北大学 | Full ceramics superhigh temperature pressure sensor and its packaging method |
| CN112459927A (en) * | 2020-10-23 | 2021-03-09 | 南京理工大学 | Y-shaped small-size bidirectional predetonation ignition tube |
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2014
- 2014-06-04 CN CN201420294056.8U patent/CN203879631U/en not_active Expired - Fee Related
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104033248A (en) * | 2014-06-04 | 2014-09-10 | 华能国际电力股份有限公司 | Ground gas turbine using pulse knocking combustion |
| CN104033248B (en) * | 2014-06-04 | 2015-10-07 | 华能国际电力股份有限公司 | A kind of ground gas turbine utilizing pulse detonation combustion |
| CN107250509A (en) * | 2015-02-17 | 2017-10-13 | 赛峰直升机发动机 | Isochoric combustion system for the turbogenerator of aircraft engine |
| CN107250509B (en) * | 2015-02-17 | 2020-07-28 | 赛峰直升机发动机 | Constant volume combustion system for a turbine engine of an aircraft engine |
| CN109154441A (en) * | 2016-05-23 | 2019-01-04 | 赛峰集团 | Toroidal combustion chamber with continuous detonation wave |
| CN107781847A (en) * | 2017-09-22 | 2018-03-09 | 中国华能集团公司 | The burner of double gaseous fuels and the gas turbine operation method using the burner |
| CN107781847B (en) * | 2017-09-22 | 2023-04-11 | 中国华能集团公司 | Dual gas fuel combustor and method of operating gas turbine using the same |
| CN110057487A (en) * | 2019-04-19 | 2019-07-26 | 中北大学 | Full ceramics superhigh temperature pressure sensor and its packaging method |
| CN110057487B (en) * | 2019-04-19 | 2020-12-01 | 中北大学 | Full-ceramic ultra-high temperature pressure sensor and packaging method thereof |
| CN112459927A (en) * | 2020-10-23 | 2021-03-09 | 南京理工大学 | Y-shaped small-size bidirectional predetonation ignition tube |
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| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20141015 Termination date: 20170604 |
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| CF01 | Termination of patent right due to non-payment of annual fee |