CN103628983B - Turbine blade of gas turbine radiation path dust guard - Google Patents
Turbine blade of gas turbine radiation path dust guard Download PDFInfo
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- CN103628983B CN103628983B CN201310689800.4A CN201310689800A CN103628983B CN 103628983 B CN103628983 B CN 103628983B CN 201310689800 A CN201310689800 A CN 201310689800A CN 103628983 B CN103628983 B CN 103628983B
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- circular cone
- cone valve
- pressure regulation
- gas turbine
- hole
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Abstract
The object of the present invention is to provide turbine blade of gas turbine radiation path dust guard, comprise pressure regulation body, optical body, optical body right-hand member is connected with pressure regulation body left end, pressure regulation body right-hand member is connected with gas turbine casing, optical body, pressure regulation body, gas turbine casing all arranges through hole, and all through holes on an axis, circular cone valve is installed in the through hole of pressure regulation body, mounting glass window on circular cone valve, in the through hole of optical body, optical fiber is set, lens, compensating chamber and inlet hole are set in pressure regulation body, inlet hole is communicated with compensating chamber, compensating chamber is connected by a point pore with the through hole of pressure regulation body, circular cone valve is arranged on the left side of point pore, circular cone valve connect live axle and can under the driving of live axle left rotation and right rotation.Glass window cleaning cycle of the present invention comparatively conventional products extends more than tens times.Meet the long term monitoring needs of commercial aviation motor, generating gas turbine.
Description
Technical field
What the present invention relates to is a kind of dust guard, specifically gas turbine blades radiation path dust guard.
Background technique
Heavy duty gas turbine has extremely important meaning in fields such as generating, ship power, petroleum production transports, relates to the fields such as material, processing, gas turbine principles and design.Heavy duty gas turbine mainly walks to introduce digestion road for development in mistake China, sets about the nineties in last century introducing.The active demand of the major areas such as the full burning of naval vessels, offshore oil, natural gas transportation, replacement coal fired power generation, gas turbine fast development has become the field that country first develops.
Gas turbine hot-end component is operated in hot environment, because the reason such as efficiency, cooling, the structural strength of the hot-end components such as turbine is more weak, once occur that individual part damages, will occur serious accident.For this reason, a lot of inspecting hole of gas turbine design, some can check the state of hot-end component in working order.Wherein at least design plural inspecting hole at high and low pressure turbine position, to measure Turbine Blade Temperature Field, coating shedding degree etc. in working order.When shutting down, also can by parts such as borescope hand inspection blades.
But the gas turbine blades thermometry of working state generally adopts radiometric temperature measurement method, receive the infrared rays of the high temperature component radiation such as blade by the highly sensitive radiation sensor of high speed, calculate the temperature of blade according to planck radiation theorem.When the temperature of the parts such as the outside directly observation blade of casing, optical focus assembly must be had to be focused on by the radiation energy of the hot-end components such as blade.Also withstand voltage, heat-resisting silica glass window must be had before optical focus assembly.Because inspecting hole position is near runner, combustion gas must be had and blow to silica glass window.Especially the sensor monitored for a long time, the contaminated probability of optical window obviously increases.The pollution level of window must be shut down cooling and be checked later, and running cannot detect.If the parameter that the temperature of the hot-end components such as blade controls as gas turbine, if measured value is lower than actual value, meaning can also increase output power again, under causing combustion engine to operate in too high operating temperature, will be very dangerous.
Typical structure is shown in accompanying drawing 1, although sweep gas blows to observation window, oppositely enters runner after running into eyeglass.During long-play, because of reasons such as residual smoke when eddy current, sweep gas instability, shutdown, can pollute eyeglass.The aeroengine of frequent start and stop is easier pollutes observation window during start and stop.
Summary of the invention
The object of the present invention is to provide and effectively can avoid carbon distribution, significant prolongation broom closet every turbine blade of gas turbine radiation path dust guard.
The object of the present invention is achieved like this:
Turbine blade of gas turbine radiation path dust guard of the present invention, it is characterized in that: comprise pressure regulation body 2, optical body 3, optical body 3 right-hand member is connected with pressure regulation body 2 left end, pressure regulation body 2 right-hand member is connected with gas turbine casing 1, optical body 3, pressure regulation body 2, gas turbine casing 1 all arranges through hole, and all through holes on an axis, circular cone valve 40 is installed in the through hole of pressure regulation body 2, mounting glass window 32 on circular cone valve 40, optical fiber 30 is set in the through hole of optical body 3, lens 31, pressure regulation body 2 li arranges compensating chamber 34 and inlet hole 35, inlet hole 35 is communicated with compensating chamber 34, compensating chamber 34 is connected by a point pore 33 with the through hole of pressure regulation body 2, circular cone valve 40 is arranged on the left side of point pore 33, circular cone valve 40 connect live axle and can under the driving of live axle left rotation and right rotation.
The present invention can also comprise:
1, described circular cone valve 40 one end is provided with groove 41, when circular cone valve 40 is positioned at initial position, the groove 41 of circular cone valve 40 is positioned at lower position, the radiant light of blade 37 is by the through hole of gas turbine casing 1, pressure regulation body 2, optical body 3 and through glass window 32, lens 31, coupled into optical fibres 30 after lens 31 focus on, sweep gas enters compensating chamber 34 by inlet hole 35, purges glass window 32 by a point pore 33; When circular cone valve 40 is behind initial position rotation alpha angle, the groove 41 of circular cone valve 40 is positioned at right positions, glass window 32 is positioned at top, the radiant light of blade 37 is stopped by groove 41, sweep gas enters compensating chamber 34 by inlet hole 35, by entering gas turbine runner through groove 41 after point pore 33; When circular cone valve 40 is after initial position rotates-α angle, the radiant light of blade 37 is stopped by the right-hand member of circular cone valve 40, and the right-hand member of circular cone valve 40 will divide pore 33 to block simultaneously.
2, the right-hand member of circular cone valve 40 is provided with spring.
Advantage of the present invention is: the present invention designs one and rotates light path valve before optical window, opens during measurement, and the radiant light of the hot-end components such as blade is through quartz window; Close when not measuring, quartz window does not contact combustion gas, and be in complete closed state, combustion gas is blocked completely, makes quartz window cleaning cycle extend more than tens times.Meet the long term monitoring needs of commercial aviation motor, generating gas turbine.
Accompanying drawing explanation
Fig. 1 is conventional turbine blade of gas turbine radiation path dust guard structural representation;
Fig. 2 is the structural representation of conical valve of the present invention when being in initial position;
Structural representation when Fig. 3 is conical valve of the present invention rotation rotation alpha angle;
Structural representation when Fig. 4 is conical valve of the present invention rotation-α angle;
Fig. 5 is the view a of circular cone valve;
Fig. 6 is the view b of circular cone valve.
Embodiment
Below in conjunction with accompanying drawing citing, the present invention is described in more detail:
Composition graphs 1 ~ 6, this device is arranged between turbine blade of gas turbine radiometric temperature measurement sensor and gas turbine.Be made up of purging valve, adpting flange, circular cone valve 40 etc.During measurement, circular cone valve 40 is opened, and radiant light enters the radiant light focusing system of temperature measurement system by circular cone valve 40.After measurement terminates, throttle down, optical lens is in sealing state, and optical lens is exposed to the time shorten under combustion gas, effectively can avoid carbon distribution, significant prolongation broom closet every.
The present invention proposes, and be arranged on rotatable circular cone valve 40 by fixing glass window 32, the axis of circular cone valve 40 is vertical with optical path direction, at circular cone valve 40 lateral opening hole.When the unthreaded hole of circular cone valve 40 aims at inspecting hole, the radiant light of blade 37 enters focusing lens 31 through glass window 32.High pressure air is passed through from the pore around glass window 32, cleaning glass, and air-flow oppositely enters inspecting hole after running into glass window 32, discharges from combustion engine runner.
At the end of measurement, circular cone valve 40 rotation alpha angle, inspecting hole is closed by circular cone valve 40, is not contacting the combustion gas or carbon distribution that may come from runner.Sweep gas, by the passage bypass of circular cone valve 40 side, enters runner, continues cooling valve body.
Prepare to shut down, or when not needing sweep gas to cool, valve rotates-α angle, and light path, gas circuit are closed simultaneously, and combustion gas and sweep gas all do not contact with glass window 32.
The operating temperature of valve body may up to 400 DEG C, and circular cone valve 40 thermal distortion can cause sealing to change, or rotational resistance increase causes rotating, and the thermal expansion of circular cone valve 40 energy self adaption, ensures the tightness of valve.In circular cone valve 40 side, stage clip is installed, ensures certain pressure.The opposite side of circular cone valve 40 is live axle, connects electronic or pneumatic rotating power.
In the face of the light path aperture of inspecting hole side is less than glass diameter, glass window 32 can not fall into combustion engine inside.Glass sheet adopts capstan nut to compress, and ensures tightness.
The present invention is made up of valve body, purging valve, rotary valve, is arranged between gas turbine inspecting hole and radiometric temperature measurement systems radiate light.Loophole in the radial direction of valve, and installs heat-resisting, withstand voltage windshield on hole, and combustion gas and optical lens are separated, radiant light passes through.The diameter of glass sheet is greater than and enters combustion engine inspecting hole diameter, can not fall into combustion engine when ensureing that eyeglass comes off.
Sweep gas enters from valve body, blows to the windshield on rotary valve, and cooling and cleaning glass window, then oppositely enter combustion engine inspecting hole runner.When valve rotation alpha angle, light path is closed, purge gas circuit closes simultaneously; As rotation-α, only close light path, sweep gas blows to rotary valve conical surface, and cooling valve body, then oppositely enters combustion engine inspecting hole runner.
The Vertical direction of light path drives light path valve, and motor or rotary cylinder are connected with light path valve by coupling shaft, drive the rotation of light path valve.
In Fig. 1, blade 37 radiant light arrives lens 31 from inspecting hole 36, glass window 32, coupled into optical fibres 30 after focusing on.Sweep gas is come in from inlet hole 35, sprays after compensating chamber 34 from around equally distributed point of pore 33, directly purges glass window 32, then enters combustion engine runner.
In Fig. 2, when circular cone valve 40 is opened, sweep gas through compensating chamber 34, point pore 33 from inlet hole 35, purges glass window 32 at a certain angle, then enters runner from rotary valve unthreaded hole 43.
In Fig. 3, after circular cone valve 40 rotation alpha, glass window 32, at confined space, no longer contacts combustion gas.Sweep gas is come in from inlet hole 35, through compensating chamber 34, point pore 33, enters runner from the groove 41 of valve body.
In Fig. 4, when circular cone valve 40 rotates-α, close blast tube, sweep gas passage and light path simultaneously.
In Fig. 5, there is a pressure spring circular cone valve 40 side, and maintain certain pressure, cover plate can be dismantled and be convenient to mounting and adjusting.In Fig. 6, opposite side is live axle, left rotation and right rotation under external means drives.
Claims (3)
1. turbine blade of gas turbine radiation path dust guard, it is characterized in that: comprise pressure regulation body (2), optical body (3), optical body (3) right-hand member is connected with pressure regulation body (2) left end, pressure regulation body (2) right-hand member is connected with gas turbine casing (1), optical body (3), pressure regulation body (2), gas turbine casing (1) all arranges through hole, and all through holes on an axis, circular cone valve (40) is installed in the through hole of pressure regulation body (2), the upper mounting glass window (32) of circular cone valve (40), optical fiber (30) is set in the through hole of optical body (3), lens (31), pressure regulation body (2) is inner arranges compensating chamber (34) and inlet hole (35), inlet hole (35) is communicated with compensating chamber (34), compensating chamber (34) is connected by a point pore (33) with the through hole of pressure regulation body (2), circular cone valve (40) is arranged on the left side of a point pore (33), circular cone valve (40) connect live axle and can under the driving of live axle left rotation and right rotation.
2. turbine blade of gas turbine radiation path dust guard according to claim 1, it is characterized in that: described circular cone valve (40) one end is provided with groove (41), when circular cone valve (40) is positioned at initial position, the groove (41) of circular cone valve (40) is positioned at lower position, the radiant light of blade (37) is by gas turbine casing (1), pressure regulation body (2), the through hole of optical body (3) through glass window (32), lens (31), coupled into optical fibres (30) after lens (31) focus on, sweep gas enters compensating chamber (34) by inlet hole (35), glass window (32) is purged by point pore (33), when circular cone valve (40) is behind initial position rotation alpha angle, the groove (41) of circular cone valve (40) is positioned at right positions, glass window (32) is positioned at top, the radiant light of blade (37) is stopped by groove (41), sweep gas enters compensating chamber (34) by inlet hole (35), enters gas turbine runner by a point pore (33) by groove (41), when circular cone valve (40) is after initial position rotates-α angle, the radiant light of blade (37) is stopped by the right-hand member of circular cone valve (40), and the right-hand member of circular cone valve (40) will divide pore (33) to block simultaneously.
3. turbine blade of gas turbine radiation path dust guard according to claim 1 and 2, is characterized in that: the right-hand member of circular cone valve (40) is provided with spring.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310689800.4A CN103628983B (en) | 2013-12-17 | 2013-12-17 | Turbine blade of gas turbine radiation path dust guard |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310689800.4A CN103628983B (en) | 2013-12-17 | 2013-12-17 | Turbine blade of gas turbine radiation path dust guard |
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| Publication Number | Publication Date |
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| CN103628983A CN103628983A (en) | 2014-03-12 |
| CN103628983B true CN103628983B (en) | 2015-09-30 |
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| CN201310689800.4A Expired - Fee Related CN103628983B (en) | 2013-12-17 | 2013-12-17 | Turbine blade of gas turbine radiation path dust guard |
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Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106644093A (en) * | 2017-01-09 | 2017-05-10 | 电子科技大学 | Method for measuring surface temperature of turbine blades based on biaxial adjustment |
| CN108547700B (en) * | 2018-04-12 | 2019-10-25 | 北京克斯特航空器材科技开发有限公司 | A kind of dust-protection type aero-engine cooling mechanism and its heat dissipating method |
| CN108872080B (en) * | 2018-08-24 | 2022-03-04 | 哈尔滨工业大学（威海） | Front light path system of plasma atomic emission spectrometer |
| CN108802009B (en) * | 2018-08-24 | 2022-03-04 | 哈尔滨工业大学（威海） | Method for detecting heavy metal by using plasma atomic emission spectrometer |
| CN112648522B (en) * | 2020-11-05 | 2022-06-07 | 中国航发沈阳发动机研究所 | Pneumatic servo control valve of dustproof aero-engine lubricating system |
| CN112983652B (en) * | 2021-03-12 | 2022-09-02 | 广州大学城华电新能源有限公司 | Gas inlet control system of gas turbine |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN101571429A (en) * | 2009-05-27 | 2009-11-04 | 北京航空航天大学 | High temperature-pressure radiation heat flow meter |
| CN102004000A (en) * | 2010-10-21 | 2011-04-06 | 华中科技大学 | Surface temperature detection system for rotation part in high-temperature high-pressure container |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20080297808A1 (en) * | 2005-12-06 | 2008-12-04 | Nabeel Agha Riza | Optical Sensor For Extreme Environments |
| US8749629B2 (en) * | 2011-02-09 | 2014-06-10 | Siemens Energy, Inc. | Apparatus and method for temperature mapping a turbine component in a high temperature combustion environment |
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2013
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Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101571429A (en) * | 2009-05-27 | 2009-11-04 | 北京航空航天大学 | High temperature-pressure radiation heat flow meter |
| CN102004000A (en) * | 2010-10-21 | 2011-04-06 | 华中科技大学 | Surface temperature detection system for rotation part in high-temperature high-pressure container |
Non-Patent Citations (1)
| Title |
|---|
| 《涡轮叶片光纤温度测量系统》;冯驰等;《应用科技》;20090731;第36卷(第7期);第33-36页 * |
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| CN103628983A (en) | 2014-03-12 |
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Granted publication date: 20150930 Termination date: 20211217 |