CN103266922B - Turbine stator blade with interstage combustor - Google Patents
Turbine stator blade with interstage combustor Download PDFInfo
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- CN103266922B CN103266922B CN201310236749.1A CN201310236749A CN103266922B CN 103266922 B CN103266922 B CN 103266922B CN 201310236749 A CN201310236749 A CN 201310236749A CN 103266922 B CN103266922 B CN 103266922B
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- guide vane
- chamber
- turbine stator
- main body
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Abstract
The invention discloses a turbine stator blade with an interstage combustor, and relates to turbine stator blades of aero-engines or gas turbines. The turbine stator blade comprises an inner ring, an outer ring and multiple guide blades, wherein the guide blades are provided with a guide blade main body and a guide blade cover; the guide blade cover is arranged on the upper end of the guide blade main body, and the guide blade main body is provided with a front oil injection cavity, a middle backflow cavity and a rear cooling cavity; another cooling cavity is formed at the rear of the guide blade cover, and the oil injection cavity is internally provided with a spraying rod slot; the cooling cavity of the guide blade main body and the cooling cavity of the guide blade cover respectively have cooling holes; the turbine stator blade is also provided with ignition devices and multiple spraying rod devices, and the ignition devices are provided with ignition bases and ignition electric nozzles; the spraying rod devices are arranged on the guide blades, the outer ends of the spraying rod devices pass through and are exposed of the outer ring, and the inner ends of the spraying rod devices stretch into oil injection cavities of the guide blades; and the spraying rod devices are provided with oil pipes, gas pipes and nozzles, oil spraying ports and multiple gas spraying ports are formed in the nozzles, and the oil pipes and the air pipes are respectively connected with an oil supplying pipe and a gas supplying pipe.
Description
Technical field
The present invention relates to the turbine stator vane of aeroengine or gas turbine, especially relate to a kind of turbine stator vane with inter-stage firing chamber.
Background technique
In order to promote the power performance of aeroengine or gas turbine, conventionally have the compressor pressure ratio of increase, improve the methods such as turbine inlet temperature, but the potentiality that this type of research can be excavated are less.
Interstage turbine burner (Interstage Turbine Burner, ITB) as a kind of new thinking in being in recent years suggested, it is by adding a firing chamber to promote circulating-heating amount between the high pressure in aeroengine and low-pressure turbine, thus lifting engine power.Because this firing chamber is disposed between two turbine stage, so than main combustion chamber, it is high that its inlet air flow temperature and speed are all wanted, and requires high to steady flame; Than tail pipe burner, owing to will considering the tenability limit of low-pressure turbine thereafter, temperature rises can not be too high, so high to poor oil firing's performance requirement; Due to the limited space between turbine stage, Combustion chamber design also needs to consider compactedness simultaneously.
Standing vortex burning chamber (Trapped Vortex Combustor, TVC) is a kind of scheme that can be used as inter-stage firing chamber.It is comprised of cavity and main flow, and air and fuel is rapid mixing burning formation recirculating zone in cavity.Due to cavity from main flow regions shield out, formed separately flame, so it can keep stable operation under very wide flox condition.The advantages such as it is wide that standing vortex burning chamber has stable operation range, and the poor superior performance of putting out is simple in structure, and disposal of pollutants is low.But it need to increase certain axial length while being applied to the burning of aeroengine inter-stage, is unfavorable for the Weight control of motor.
Publication number be CN1858498 Patent Application Publication a kind of tangential standing vortex burning chamber, utilize the high centrifugal acceleration that tangential swirl produces to strengthen spray combustion, the position before combustor exit is provided with blending hole and distributes to guarantee its good outlet temperature.
Ultra-compact firing chamber (Ultra-Compact Combustior, UCC) is the scheme that the another kind that proposed by the Air Force Research Laboratory (Air Force Research Laboratory, AFRL) for 2002 can be used as inter-stage firing chamber.Its structure characteristic is along circumferential arrangement, to have a toroidal cavity on Turbomachinery casing outer shroud, similar TVC scheme.In cavity, air-flow is around axis rotational flow, strengthens the blending of oil gas and combustion gas, and the centrifugal force producing due to rotational flow causes the existence of radial pressure gradient, also strengthened the footpath combustion gas that makes progress and propagated.Tangential cavity provides enough residence times for fuel-rich combustion, and the cycle rotation of products of combustion has also been stablized flame.High centrifugal force can be accelerated velocity of propagation of flame to a certain extent, and this all has greatly improved to combustion efficiency and combustion stability.And near axis roulette speed is little, form low velocity zone, can be used as stable high temperature source.Flame propagates in axial main flow by the groove of special shape on stator blade.In simple terms, tangential cavity can be regarded as to main burning region, the radial groove on blade is zone line, and the Ze Shi dilution zone, blade rear portion of main flow.The great advantage of UCC scheme is can be suitable with turbine stator vane axial dimension, only increases a small amount of radial space and non-axial occupation space does not increase separate part simultaneously, has avoided causing the increase of motor overall weight.No matter but be at present that experimental research or numerical simulation are all in the preliminary stage about UCC.
Summary of the invention
The object of this invention is to provide and can overcome that inlet air flow flow velocity is large, high the produced difficulty of temperature, can solve poor oil firing, the problems such as steady flame and blade are cooling, there is good fuel-lean blowout characteristic, can significantly improve a kind of turbine stator vane with inter-stage firing chamber of atomizing effect, reduction blockage ratio.
The present invention includes interior ring, outer shroud and a plurality of guide vane; Be equipped with cooling chamber outward, cooling chamber is provided with suction port, and each guide vane is located between interior ring and outer shroud, is sprue between each guide vane; Its feature is:
Guide vane is provided with guide vane main body and guide vane lid, and guide vane is covered on guide vane main body upper end, and guide vane main body is provided with the refluxing chamber at anterior fuel injection chamber, middle part and the cooling chamber at rear portion; Guide vane postoperculum is also provided with cooling chamber, and there is spray boom slot fuel injection chamber inside, and fuel injection chamber is communicated with sprue; The cooling chamber of guide vane main body is communicated with the cooling chamber of guide vane lid and the cooling chamber of outer shroud, and the cooling chamber of the cooling chamber of guide vane main body and guide vane lid is equipped with Cooling Holes;
The described turbine stator vane with inter-stage firing chamber is also provided with ignition mechanism and a plurality of spray rod device, and ignition mechanism is provided with igniting seat and ignition electric nozzle, and igniting seat is arranged on outer shroud, and ignition electric nozzle is fixed on the cooling chamber that outer shroud was gone up and passed to igniting seat; Spray rod device is arranged on described guide vane, spray rod device outer end is passed and is exposed outer shroud, the fuel injection chamber of guide vane is stretched in spray rod device the inner, spray rod device is provided with oil pipe, tracheae and nozzle, and oil pipe is located at tracheae inside, and nozzle is located on oil pipe and tracheae, nozzle is provided with jet and a plurality of puff prot, jet is communicated with oil pipe, and each puff prot is all communicated with tracheae, and oil pipe is connected with air supply pipe with fuel supply line respectively with tracheae.
Described igniting seat and ignition electric nozzle generally can be established 2; Described spray rod device generally can be established 6～12, and is uniform setting.The quantity of spray rod device and guide vane quantity correspondent equal.
The jet of described nozzle is preferably located at nozzle central authorities, and puff prot can be provided with 4, and 4 inclined holes that puff prot is biasing, are all laid in jet periphery.
Described fuel injection chamber tail end is provided with baffle plate, is provided with narrow slit before baffle plate, and by narrow slit, fuel injection chamber is communicated with sprue.Described baffle plate is to be the dihedral baffle plate of 120 °.
Compared with the prior art, beneficial effect of the present invention is as follows:
Owing to adopting technique scheme, the present invention can be transformed into the guide vane of low-pressure turbine the inter-stage firing chamber with steady flame effect.Nozzle is to the anterior fuel injection chamber ejection of guide vane gas mixture, and atomized fuel is at guide vane internal surface evaporation endothermic, and the effect that can play cooled blade can make again gasification of fuel oil be beneficial to burning.By igniting, can realize between turbine stator vane and burning, promote the power of whole motor.Adopt pneumatic atomizer oil spout, atomizing effect is good, has good fuel-lean blowout characteristic; Individual blade is transformed into a flame holder, blockage ratio has been dropped to minimum.Utilize the steady flame effect of the refluxing chamber at guide vane middle part, can realize in the success of high velocity air down-firing and widen stable operation border.
As can be seen here, the present invention has following outstanding advantages:
(1) with inter-stage firing chamber, can supplement the acting loss of high-temperature fuel gas after high-pressure turbine expands, by tissue, burn and increase the temperature rise of combustion gas, improve combustion gas acting ability, and then improve motor complete machine power;
(2) do not need to increase axial length and radial length, structure is comparatively simple, occupies volume little, for the weight increase that whole motor brings also less;
(3) fueling injection equipment adopts pneumatic atomizer structure, combines fuel evaporation and guide vane are cooling, has improved the combustion efficiency of fuel oil;
(4) guide vane afterbody is provided with Cooling Holes structure, and cooled gas flows into burning gallery from cooling chamber passage, forms one deck film overcast guide vane afterbody, and cooled gas also can be strengthened the blending of zone of combustion and main flow simultaneously.
(5) each puff prot is the inclined hole of biasing, and air-flow can not converge towards any like this, but the very little distance of setovering along clockwise direction separately, thereby eddy flow is produced, can strengthen like this atomizing of air-flow to fuel oil.
Accompanying drawing explanation
Fig. 1 is the surface structure schematic diagram of the embodiment of the present invention.
Fig. 2 is the sectional structure schematic diagram of the embodiment of the present invention.
Fig. 3 is the guide vane of the embodiment of the present invention and the surface structure schematic diagram of spray rod device.
Fig. 4 is the structure schematic top plan view of guide vane main body of the guide vane of the embodiment of the present invention.
Fig. 5 is the sectional structure schematic diagram of Fig. 3.
Fig. 6 is the spray rod device surface structure schematic diagram in Fig. 3.
Fig. 7 be the embodiment of the present invention nozzle face structural representation.
Embodiment
Referring to Fig. 1～7, the embodiment of the present invention is provided with outer shroud 1, directing vane lamellar body guide vane main body 2, guide vane lid 3,4,2 ignition mechanisms of interior ring (comprising igniting seat 7 and ignition electric nozzle (not shown in FIG.)) and 8 spray rod devices 6 and forms.
Outer shroud 1 is provided with cooling chamber 11, and cooling chamber 11 is provided with suction port 5.Guide vane is located between interior ring 4 and outer shroud 1, and guide vane is provided with guide vane main body 2 and guide vane lid 3, and guide vane lid 3 is located at guide vane main body 2 upper-end surfaces.Guide vane main body 2 is provided with the refluxing chamber 204 at anterior fuel injection chamber 201, middle part and the cooling chamber 205 at rear portion; There is spray boom slot 207 fuel injection chamber 201 inside, and fuel injection chamber 201 tail ends are provided with baffle plate 202, and baffle plate 202, for to be the dihedral baffle plate of 120 °, is provided with narrow slit 203 before baffle plate 202, and narrow slit 203 is connected fuel injection chamber with sprue.Guide vane lid 3 is fixed in guide vane main body 2 upper ends, and fuel injection chamber 201, refluxing chamber 204 are all only located at guide vane main body 2, and cooling chamber 205 extends on guide vane lid 3 and is communicated with the cooling chamber 11 of outer shroud.Refluxing chamber 204 is main recirculating zone, has jointly formed a flame holder with guide vane lid 3.The wall that guide vane main body 2 and guide vane cover 3 common cooling chamber 205 both sides be provided with the 2 row's Cooling Holes 206(2 row Cooling Holes 206 that are axially acute angle all be axially 30 °, diameter 1mm).
Igniting seat 7 is arranged on outer shroud 1, and ignition electric nozzle (not shown in FIG.) is fixed on igniting seat 7 and puts in sprue through outer shroud cooling chamber 11.
8 spray rod devices 6 are uniform setting.Each spray rod device 6 correspondence is arranged in 1 guide vane guide vane main body 2.Spray rod device 6 outer ends through and expose outer shroud 1, fuel injection chamber 201 is stretched in spray rod device 6 the inners, spray rod device 6 is provided with oil pipe 602, tracheae 601 and nozzle 603, oil pipe 602 is located at tracheae 601 inside, nozzle 603 is located on oil pipe 602 and tracheae 601, nozzle 603 is provided with jet 604 and 4 puff prots 605, jet 604 is communicated with oil pipe 602, each puff prot 605 is all communicated with tracheae 601, and oil pipe 602 is connected with air feeder (not shown in FIG.) with extraneous oil supplying device (not shown in FIG.) respectively with tracheae 601.
8 spray rod devices 6 are uniform setting.The jet 604 of nozzle 603 is located at nozzle 603 central authorities, 4 inclined holes that puff prot 605 is biasing, and be all laid in jet 604 peripheries.
The present embodiment working principle is as follows:
The tracheae 601 of spray rod device 6 is introduced high-pressure air by extraneous air feeder (as gas compressor), from 4 puff prot 605 high speeds, sprays into fuel injection chamber 201, and fuel oil is introduced by extraneous oil supplying device and sprayed into fuel injection chamber 201 from jet 604.4 bundle gases are with the common directive fuel oil of slightly off-centered direction, make the rapid atomization of fuel oil, produce the rotary fluid mist of some strength simultaneously, liquid mist impinges upon the head of fuel injection chamber 201 subsequently, because the leading edge of the outer surface (being guide vane 2) of fuel injection chamber 201 is directly in the face of high temperature incoming flow, therefore the wall surface temperature of whole fuel injection chamber 201 is all higher.And the air temperature of ejection is relatively low from puff prot 605, air high speed impact wall can play cooling effect, and liquid mist impinges upon evaporation endothermic on wall simultaneously, can strengthen the evaporation of fuel oil again by cooling wall.Gas mixture after interacting with wall finally sprays into sprue from tail end baffle plate 202 narrow slit 203 above, there is part mixture to enter the refluxing chamber 204 at guide vane 2 middle parts, in refluxing chamber 204, form a stable recirculating zone among a small circle, also have part mixture to enter sprue, mix with the high-temperature fuel gas of main flow, in the sprue near refluxing chamber 204 rear portions, burn.Different from the middle part oil spout of rearmounted body from a kind of trapped vortex combustor of introducing in China Patent Publication No. CN1784574A, the embodiment of the present invention adopts pneumatic atomizer spray rod device 6 fuel feeding, fuel oil first fully sprays into main flow from anterior both sides again after atomization in fuel injection chamber 201, and most fuel oil is burned consumption in main flow.Refluxing chamber 204 has played the effect of connection flame when igniting in addition.
Cooled gas enters outer shroud cooling chamber 11 from cooling chamber suction port 5, enters subsequently in the rear portion cooling chamber 205 of each guide vane 2, and a plurality of Cooling Holes 206 set by cooling chamber 205 both sides enter main flow.Notice that flame of combustion mainly appears at the rear portion of guide vane 2, and can form at guide vane 2 rear portions attached wall air film from each Cooling Holes 206 cold air jet out, thereby by guide vane 2 and high-temperature fuel gas isolation, guaranteed the reliably working of guide vane 2.Each cooling air jet has been strengthened the horizontal disturbance of main flow simultaneously, has promoted thus the blending of each component in flow field, and the temperature distribution that is conducive to flow field outlet is tending towards even.
Claims (6)
1. with a turbine stator vane for inter-stage firing chamber, comprise interior ring, outer shroud and a plurality of guide vane; Be equipped with cooling chamber outward, cooling chamber is provided with suction port, and each guide vane is located between interior ring and outer shroud, is sprue between each guide vane; It is characterized in that:
Guide vane is provided with guide vane main body and guide vane lid, and guide vane is covered on guide vane main body upper end, and guide vane main body is provided with the cooling chamber of the fuel injection chamber of leading edge, the refluxing chamber at middle part and trailing edge; Guide vane postoperculum is also provided with cooling chamber, and there is spray boom slot fuel injection chamber inside, and fuel injection chamber is communicated with sprue; The cooling chamber of guide vane main body is communicated with the cooling chamber of guide vane lid and the cooling chamber of outer shroud, and the cooling chamber of the cooling chamber of guide vane main body and guide vane lid is equipped with Cooling Holes;
The described turbine stator vane with inter-stage firing chamber is also provided with ignition mechanism and a plurality of spray rod device, and ignition mechanism is provided with igniting seat and ignition electric nozzle, and igniting seat is arranged on outer shroud, and ignition electric nozzle is fixed on the cooling chamber that outer shroud was gone up and passed to igniting seat; Spray rod device is arranged on described guide vane, spray rod device outer end is passed and is exposed outer shroud, the fuel injection chamber of guide vane is stretched in spray rod device the inner, spray rod device is provided with oil pipe, tracheae and nozzle, and oil pipe is located at tracheae inside, and nozzle is located on oil pipe and tracheae, nozzle is provided with jet and a plurality of puff prot, jet is communicated with oil pipe, and each puff prot is all communicated with tracheae, and oil pipe is connected with air supply pipe with fuel supply line respectively with tracheae.
2. a kind of turbine stator vane with inter-stage firing chamber as claimed in claim 1, is characterized in that: described ignition mechanism is provided with 2.
3. a kind of turbine stator vane with inter-stage firing chamber as claimed in claim 1, is characterized in that: described spray rod device is provided with 6～12, and is uniform setting.
4. a kind of turbine stator vane with inter-stage firing chamber as claimed in claim 1, is characterized in that: the jet of described nozzle is located at nozzle central authorities, and described puff prot is provided with 4,4 inclined holes that puff prot is biasing, and be all laid in jet periphery.
5. a kind of turbine stator vane with inter-stage firing chamber as claimed in claim 1, is characterized in that: described fuel injection chamber tail end is provided with baffle plate, is provided with narrow slit before baffle plate, and by narrow slit, fuel injection chamber is communicated with sprue.
6. a kind of turbine stator vane with inter-stage firing chamber as claimed in claim 5, is characterized in that: described baffle plate is to be the dihedral baffle plate of 120 °.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310236749.1A CN103266922B (en) | 2013-06-15 | 2013-06-15 | Turbine stator blade with interstage combustor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310236749.1A CN103266922B (en) | 2013-06-15 | 2013-06-15 | Turbine stator blade with interstage combustor |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103266922A CN103266922A (en) | 2013-08-28 |
| CN103266922B true CN103266922B (en) | 2014-11-12 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201310236749.1A Expired - Fee Related CN103266922B (en) | 2013-06-15 | 2013-06-15 | Turbine stator blade with interstage combustor |
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Families Citing this family (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104832948A (en) * | 2015-04-23 | 2015-08-12 | 中国人民解放军空军工程大学 | Fingerprint mesh cooling device for concave cavity combustion chamber |
| CN104847498B (en) * | 2015-05-27 | 2016-04-06 | 厦门大学 | The inter-stage firing chamber of water conservancy diversion integration in whirlpool |
| CN105546579A (en) * | 2015-12-25 | 2016-05-04 | 中国航空工业集团公司沈阳发动机设计研究所 | Fuel-oil spray nozzle |
| CN108758693A (en) * | 2018-04-16 | 2018-11-06 | 西北工业大学 | A kind of integrated after-burner with double oil circuits and butt center wimble structure |
| CN112228168B (en) * | 2020-10-21 | 2022-09-30 | 中国航发沈阳发动机研究所 | Gas collection drainage structure for cooling inner cavity of stator blade |
| CN113202566B (en) * | 2021-04-19 | 2022-12-02 | 中国航发湖南动力机械研究所 | Turbine guide vane and gas turbine engine |
| CN115013839A (en) * | 2022-05-12 | 2022-09-06 | 中国航发四川燃气涡轮研究院 | Afterburning chamber fuel spray lance structure |
| CN115451427B (en) * | 2022-09-01 | 2023-10-27 | 中国航发湖南动力机械研究所 | Interstage combustion chamber and turbofan engine with same |
| CN116428615B (en) * | 2023-05-23 | 2024-05-10 | 浙江大学 | Circumferential circulation combustor between turbine stages |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| BE755567A (en) * | 1969-12-01 | 1971-02-15 | Gen Electric | FIXED VANE STRUCTURE, FOR GAS TURBINE ENGINE AND ASSOCIATED TEMPERATURE ADJUSTMENT ARRANGEMENT |
| EP0924470B1 (en) * | 1997-12-19 | 2003-06-18 | MTU Aero Engines GmbH | Premix combustor for a gas turbine |
| US7762073B2 (en) * | 2006-03-01 | 2010-07-27 | General Electric Company | Pilot mixer for mixer assembly of a gas turbine engine combustor having a primary fuel injector and a plurality of secondary fuel injection ports |
| CN100443806C (en) * | 2006-05-16 | 2008-12-17 | 北京航空航天大学 | Tangential standing vortex burning chamber |
| CN100510541C (en) * | 2007-06-27 | 2009-07-08 | 北京航空航天大学 | Single-vortex combustion chamber |
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2013
- 2013-06-15 CN CN201310236749.1A patent/CN103266922B/en not_active Expired - Fee Related
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| CN103266922A (en) | 2013-08-28 |
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Granted publication date: 20141112 Termination date: 20200615 |