CN104019465A - Turbine-based combined cycle engine super-combustion chamber - Google Patents
Turbine-based combined cycle engine super-combustion chamber Download PDFInfo
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- CN104019465A CN104019465A CN201410231348.1A CN201410231348A CN104019465A CN 104019465 A CN104019465 A CN 104019465A CN 201410231348 A CN201410231348 A CN 201410231348A CN 104019465 A CN104019465 A CN 104019465A
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Abstract
The invention discloses turbine-based combined cycle engine super-combustion chamber. Key parts of the super-combustion chamber comprise a shunt ring, a rear area-variable deflation valve, a flow guide tongue piece, a square lobe mixer, a first area fuel ejector, a center cone, a second area fuel injection ring, an evaporation tube flame stabilizer, a heat-isolating screen, a super-combustion chamber cylinder, an outer extending groove-width-variable radial flame stabilizer and an inner extending radial flame stabilizer. An internal flow field of the super-combustion chamber is reasonably distributed, the phenomenon of backflow from a punching duct to a turbofan duct can not occur, flow separation can not occur in the square lobe mixer, and the evaporation tube flame stabilizer can achieve soft ignition of the super-combustion chamber. The whole super-combustion chamber is high in mixing efficiency, little in cold flow resistance, high in combustion efficiency, reasonable in temperature distribution, and capable of meeting use requirements in a whole flight envelope of the super-combustion chamber in each work state and the requirement for boost of an turbofan ramjet.
Description
Technical field
The invention belongs to airbreathing motor technical field, particularly a kind of turbine base combined cycle engine.
Background technology
Turbine base combined cycle engine (be called for short TBCC) as a kind of airbreathing motor have that flight range is wide, CTOL and the performance advantage such as reusable be considered to most promising hypersonic aircraft power set of present stage.Be successfully applied to after SR-71 blackbird reconnaissance plane from TBCC prototype J58 the earliest in the world, countries in the world all start to drop into a large amount of manpowers, financial resources carries out the research and development of the hypersonic power set of combined type, especially plans achievement with the RTA plan of U.S. NASA and Japanese HYPR remarkable.
At present domestic to the research and development of turbine base combined cycle engine also in the starting stage, and between the U.S. and Japan, there is very large technological gap.Its operation mode, operation principle, MODAL TRANSFORMATION OF A process etc. are made to some preliminary conceptual approaches, not the particular problem such as the work engagement process between method for designing, the different operating mode of in-depth analysis research turbine base combined cycle engine and different designs parameter, the impact of adjusting rule on engine performance.Especially to both as the after-burner under TBCC turbofan pattern, press the design of super combustion chamber of combustion chamber and the document that specific implementation is not also published as punching press pattern undershoot again.
Than traditional after-burner and stamping combustion chamber, mainly there are following technological difficulties in the design of super combustion chamber:
(1) the inside and outside blending of containing two strands of air-flows: structure, lobed mixer is in the past all direct and flow splitter joins, in the time there is certain axial distance between the two, have compared with the lobed mixer of large expansion angle and easily occur flow separation in lobe inside, impact flows to the formation in whirlpool; Flox condition, the great majority of forefathers' research are all under the flow regime of after-burner, the turbofan pattern of this flox condition and TBCC is close, and the whole working range main duct of TBCC is larger especially than changing, become particularly important so suppress the refluence of engine under the punching press pattern of larger bypass ratio.Therefore, take into account bypass ratio and change high-efficiency low-resistance under the each mode of operation in super combustion chamber greatly and be mixed into the top priority of its burning tissue.
(2) reliable ignition and flame stabilization: super combustion chamber is that flow parameter excursion is large than a distinguishing feature of traditional aeroengine combustor buring chamber, its low temperature, at a high speed, low pressure range is wider, realize reliable ignition under low-resistance at whole flight envelope scope intrinsic motivation, pass flame and flame stabilization more difficult.
(3) between oil injection structure and mixing machine, flameholder, mate design: in order to realize the efficient burning under the each mode of operation in super combustion chamber, between the fuel nozzle layout that need to have an innovation and flameholder and mixing machine, mate, make the mixed gas in combustion zone, flameholder rear there is the oil-gas ratio that is applicable to burning and passes flame.
Therefore, the design of super combustion chamber has the difficult point of himself technically.In the technical foundation of existing aeroengine combustor buring chamber, the burning organization scheme that designs the super combustion chamber of above-mentioned 3 technological difficulties of the fine solution of a kind of energy is very important.
Summary of the invention
The problem to be solved in the present invention is to provide the super combustion chamber of a kind of turbine base combined cycle engine, this combustion chamber has the features such as cold conditions flow resistance is little, efficiency of combustion is high, Temperature Distribution is reasonable, can meet steady operation and the propulsive performance requirement of TBCC under each operation mode in whole flight envelope.
The super combustion chamber of a kind of turbine base combined cycle engine of the present invention, comprise flow splitter, rear variable area vent valve, water conservancy diversion tongue piece, square lobed mixer, center cone, be arranged on fueller on center cone and flameholder, heat screen, super combustion chamber cylindrical shell covers on outermost layer; Between described square lobed mixer and flow splitter, separate, exist wheelbase from; Water conservancy diversion tongue piece is fixed in runner, and after being next to rear variable area vent valve, is right against square lobed mixer trough top with discrete shape.
As the further improvement of technique scheme, described flameholder mainly by evaporation tubular type flameholder, be arranged on evaporation tubular type flameholder outer rim overhanging change groove width radially flameholder and be arranged on evaporation tubular type flameholder inner side in stretch radially flameholder and form, its blockage ratio is 43.6%; Evaporation tubular type flameholder comprises Fuel Injector Bar on duty, oil splasher, air entraining pipe, pre-gas inlet, fuel-rich mixed gas venthole, evaporation tube and V-type groove; There is the angle of sweep of 45 ° ~ 60 ° in some overhanging change groove widths radially flameholder and super combustion chamber axis, be evenly fixed on V-type groove, and larger near the groove width at cylindrical shell place, super combustion chamber, less near the groove width at V-type groove place; Inside stretch radially stabilizer and be fixedly connected on center cone tail end.
As the further improvement of technique scheme, described fueller comprises I district Fuel Injector Bar, II district injection loop and described Fuel Injector Bar on duty; I district Fuel Injector Bar is positioned at square lobe mixer outlet, and with just right in square lobed mixer dividing plate.
As further improving again of technique scheme, described square lobed mixer such as adopts up and down not at the lobe of the angle of flare.
As further improving again of technique scheme, the number of described water conservancy diversion tongue piece is identical with the lobe number of square lobed mixer, and its flow-deviation angle equates with the lobed mixer trough place angle of flare.
As further improving again of technique scheme, described center cone surface is spheroid shape, and jointly completes the blending task of super combustion chamber with water conservancy diversion tongue piece and square lobed mixer.
As further improving again of technique scheme, described I district Fuel Injector Bar adopts circumferential side spray, and II district injection loop adopts radially side spray, and Fuel Injector Bar on duty adopts radial spray mode.
The super combustion chamber of turbine base combined cycle engine provided by the invention has the following advantages:
1. the super combustion chamber of turbine base combined cycle engine provided by the invention, can solve super combustion chamber well than the distinctive key technology difficult point of traditional after-burner.Each part design is reasonable, and the Flow Field Distribution under each mode of operation of super combustion chamber is reasonable, and ignition temperature distributes rationally, can meet the propelling requirement of turbine base combined cycle engine.
2. the super combustion chamber of turbine base combined cycle engine provided by the invention, designed mixing chamber can be taken into account bypass ratio and change the high-efficiency low-resistance in super combustion chamber greatly time and mix.On the one hand, square lobe internal mixer there will not be flow separation phenomenon; On the other hand, under the larger punching press state of bypass ratio, there will not be the refluence phenomenon to turbofan duct by punching press duct, can not bring excessive fluid resistance loss.Designed evaporation tubular type flame on duty stabilizer has more superior oil-poor igniting and fuel-lean blowout performance, can ensure " soft ignition " performance of super combustion chamber.Overhanging change groove width radially flameholder has good combustion stability and passes flame characteristic, can accelerate radially the crossing of flame front between flameholder of two overhanging change groove widths, improves the efficiency of combustion in super combustion chamber.
3. the super combustion chamber of turbine base combined cycle engine provided by the invention, the scientific arrangement between mixing chamber, flameholder and nozzle arrangements is reasonable.The momentum and the energy hybrid that flow to air-flow between vortex strength turbofan duct and punching press duct that mixing chamber produces, and under the effect that flows to whirlpool, promote blending between most fuel oils and air, form mixed gas comparatively uniformly and enter the participation burning of flameholder rear.Such layout is except being conducive to the evaporation of fuel oil, blending between fuel oil and air, make to form outside the oil-gas ratio that is applicable to burning after flameholder, also help ignition performance and the radially raising of stabilizer flame holding of overhanging change groove width of evaporation tubular type flame on duty stabilizer.
Brief description of the drawings
Fig. 1 is the super chamber structure schematic diagram of turbine base combined cycle engine of the present invention;
Fig. 2 a is evaporation tubular type flameholder structural perspective, and Fig. 2 b is evaporation tubular type flameholder structure front view;
Fig. 3 a and Fig. 3 b are square lobed mixer 4, flameholder and nozzle arrangements coupling schematic diagram; Fig. 3 a is front view, and Fig. 3 b is stereogram;
Fig. 4 is numerical simulation motion pattern under the each duty in the super combustion chamber of turbine base combined cycle engine, and wherein, Fig. 4 a is turbofan mode, and before Fig. 4 b is MODAL TRANSFORMATION OF A, after Fig. 4 c is MODAL TRANSFORMATION OF A, Fig. 4 d is punching press mode;
Fig. 5 is that the each operation mode in the super combustion chamber of turbine base combined cycle engine is in love along journey flow resistance coefficient change curve;
Fig. 6 be under typicalness point the super combustion chamber of turbine base combined cycle engine along journey Temperature Distribution cloud atlas;
Fig. 7 is the each radius distribution schematic diagram in the super combustor exit of turbine base combined cycle engine cross section;
Fig. 8 is the temperature distribution history of the each radius in turbine base combined cycle engine super combustor exit cross section in Fig. 7.
Detailed description of the invention
Below in conjunction with accompanying drawing, the super combustion chamber of turbine base combined cycle engine that the present invention is proposed is elaborated.
As shown in Figure 1, the super combustion chamber of a kind of turbine base combined cycle engine disclosed by the invention comprises flow splitter 1, rear variable area vent valve 2, water conservancy diversion tongue piece 3, square lobed mixer 4, center cone 6, be arranged on fueller on center cone 6 and flameholder, heat screen 9, and super combustion chamber cylindrical shell 10 covers on outermost layer.Described square lobed mixer 4 such as adopts up and down not at the lobe of the angle of flare, and separates between flow splitter 1, exist certain wheelbase from; Water conservancy diversion tongue piece 3 is fixed in runner, and after being next to rear variable area vent valve 2, is right against square lobed mixer 4 trough tops with discrete shape, and its flow-deviation angle equates with the lobed mixer 4 trough place angles of flare.The lobe of described square lobed mixer 4 and water conservancy diversion tongue piece 3 numbers are 10.Described center cone 6 surfaces are spheroid shape, and and water conservancy diversion tongue piece 3 and square lobed mixer 4 jointly complete the blending task between the air-flow of two strands of super combustion chambers.Two strands of air-flows produce the radial velocity component mutually penetrating under the special profile effect of square lobed mixer 4, and form and flow to whirlpool in square lobed mixer 4 downstreams, and air-flow carries out the exchange of quality, momentum and energy under the effect that flows to whirlpool, strengthening blending.But because super Combustion chamber design requires to have certain axial distance between square lobed mixer 4 and flow splitter 1, and the square lobed mixer trough place angle of flare is larger, easily there is flow separation phenomenon in square lobed mixer 4 inside, impact flows to the generation in whirlpool, pitot loss increases, and mixing efficiency declines.Therefore, arrange with the water conservancy diversion tongue piece 3 of trough angle of flare same airflow deflection angle and suppress flow separation in square lobed mixer 4 trough corresponding positions.Even 10 of the lobe number of the lobed mixer in the present invention and water conservancy diversion tongue piece number are in order to match with flame stabilization tank number, can to select according to the actual requirements the number of lobe number and water conservancy diversion tongue piece.
As shown in Fig. 2 a, 2b, Fig. 3 a and Fig. 3 b, described flameholder by evaporate tubular type flameholder 8, overhanging change groove width radially flameholder 11 and in stretch radially flameholder 12 and form, its blockage ratio is " soft ignition " performance requirement that 43.6%. evaporation tubular type flameholder 8 is realized in super combustion chamber, comprises Fuel Injector Bar 8-1 on duty, oil splasher 8-2, air entraining pipe 8-3, pre-gas inlet 8-4, fuel-rich mixed gas venthole 8-5, evaporation tube 8-6 and V-type groove 8-7.Evaporation tubular type flameholder 8 is loopful shape in super combustion chamber, is arranged in intension air-flow, is mainly used in the incendiary source that provides stable.10 overhanging change groove widths radially flameholder 11 are evenly fixed on V-type groove 8-7, and the groove width near cylindrical shell 10 places, super combustion chamber is larger, groove width near V-type groove 8-7 place is less, layout is conducive to pass between groove flame like this, the flame front of 11 of overhanging change groove width flameholders is crossed as early as possible, improve efficiency of combustion, shorten super chamber length, make super combustor exit Temperature Distribution reasonable.There is the angle of sweep of 45 ° ~ 60 ° with super combustion chamber axis in overhanging change groove width radially flameholder 11, the arrangement at 45 ° ~ 60 ° of angles of sweep is too to concentrate for fear of the heat release on the axis of super combustion chamber the heat release pulsation causing, suppress the generation of low-frequency oscillation burning, best results in the time that angle of sweep is 60 °.Each overhanging change groove width radially stabilizer 11 is all right against the trough of square lobed mixer 4, makes to stablize tank and flows overlay area in high-temperature fuel gas.In 2, stretching radially stabilizer 12 is fixedly connected on the V-type groove 8-7 of center cone 6 tail ends.Overhanging change groove width radially stabilizer 11 and in stretch radially stabilizer 12 for the flame stabilization of super combustion chamber under each operating mode.
The operation principle of evaporation tubular type flameholder is: fuel oil is fed by Fuel Injector Bar 8-1 on duty, is sprayed onto oil splasher 8-2 upper, carries out first atomization under Aerodynamic force action, after first atomization, forms oil droplet not of uniform size.Oil droplet moves downstream with air-flow and be subject to thermal evaporation in evaporation tube 8-6 in air entraining pipe 8-3, form the mixed gas of rich oil via fuel-rich mixed gas venthole 8-5 ejection, unevaporated oil droplet forms oil film at fuel-rich mixed gas venthole wall, and atomization again under the Aerodynamic force action of pre-combustion gas.Because the mixed gas of fuel-rich mixed gas venthole ejection and the angle of pre-fuel gas flow direction are 45 ° ~ 90 ° (in Fig. 2 b with 60 ° of signals), the mixed gas jet of fuel-rich mixed gas venthole ejection is better with pre-gas mixing, be mixed into the premix gas that is applicable to ignition and combustion, enter the low speed recirculating zone at V-type groove rear, ignition in recirculating zone.Because evaporation tube 8-6 is better to the atomizing effect of fuel oil, therefore evaporate tubular type flameholder 8 and there is good oil-poor igniting and extinguishment characteristics.The fuel delivery (igniting oil-gas ratio) of Fuel Injector Bar 8-1 on duty can independently be controlled, so the oil-poor igniting requirement can adapt in super combustion chamber to regulate flox condition to change greatly time.
The super combustion chamber of described turbine base combined cycle engine, adopts subregion fuel feeding.Fueller comprises I district Fuel Injector Bar 5, II district injection loop 7 and described Fuel Injector Bar 8-1 on duty, and fuel delivery accounts for respectively 75%, 15% and 10% of total fuel delivery, all adopts the simple nozzle fuel feeding of 0.5mm.I district Fuel Injector Bar 5 is positioned at square lobed mixer 4 and exports, and with just right in square lobed mixer 4 dividing plates.I district Fuel Injector Bar 5 has 54 nozzles, adopts circumferential side spray, respectively to becoming the radially area spray of flameholder (11) both sides of groove width.II district injection loop 7 is evenly arranged 10 nozzles, adopts radially side spray.Fuel Injector Bar 8-1 on duty has 10 nozzles, adopts radial spray mode atomization in oil splasher and evaporation tube.
Between described square lobed mixer 4, flameholder and nozzle arrangements, be that coupling is arranged.Described evaporation tubular type flameholder 8 is arranged in the high temperature gas flow of turbofan duct, in addition, Fuel Injector Bar 8-1 on duty is arranged in square lobed mixer 4 crest height of wave warm airs, be conducive to the evaporation of fuel oil in Fuel Injector Bar 8-1 on duty, these are all favourable to flame stabilization and the igniting of evaporation tubular type flameholder 8.Each described overhanging change groove width radially stabilizer 11 is all right against in the crest height of wave warm air of square lobed mixer, and gas flow temperature is high is conducive to the radially raising of stabilizer 11 flame holdings of overhanging change groove width.I district Fuel Injector Bar 5 is positioned at the crest region that square lobed mixer 4 exports, and near partition position, adopts circumferential side spray, to the radially area spray between stabilizer 12 of two overhanging change groove widths.Because the fuel delivery of I district Fuel Injector Bar 5 accounts for overwhelming majority's (75%) of total fuel delivery, the distribution situation of this part fuel oil in super combustion chamber directly affects the combustibility of super combustion chamber, therefore this part fuel oil is exported to infeed at described square lobed mixer 4, under the induced effect that flows to whirlpool, strengthen the blending between oil gas, spray orifice is arranged near the internal partition of crest region, can utilize the thermal current at crest place to fuel Heating, be conducive to the evaporation of fuel oil, for combustion zone, flameholder rear creates favorable conditions.
Performance to the super combustion chamber of turbine base combined cycle engine of the present invention is verified:
Adopt the method for numerical simulation to study the flow field of the super combustion chamber of turbine base combined cycle engine provided by the invention.Adopt SIMPLE algorithm based on pressure, carry out for every employing Second-order Up-wind form of governing equation discrete, the Realizable k-ε model that turbulence model is selected, wall uses non-equilibrium Wall-function to process.The boundary condition using in numerical simulation comprises: the import of turbofan duct and the import of punching press duct all adopt mass flow import, and computational fields outlet adopts pressure export, and sector crosssection two sides adopt periodic boundary condition.Import and export boundary condition parameter and determine according to the different operating condition of super combustion chamber, the high-temperature fuel gas of turbofan import is given by the mass fraction of given oxygen, carbon dioxide and steam.Fig. 4 a-4d is the motion pattern under the each operation mode in super combustion chamber under numerical simulation.Can be found out by motion pattern, under each operating mode, lobed mixer inside all occurs without flow separation phenomenon.Lobed mixer trailing edge place's crest and trough corresponding position are without refluence, and the VELOCITY DISTRIBUTION while entering stabilizer is substantially even.Illustrate that the mixing chamber in the present invention is reasonable in design, can take into account the efficient blending under each operating mode, do not transferring to completely under press work pattern, lobed mixer can play the effect of efficient blending, is conducive to improve efficiency of combustion; And under punching press state, can effectively suppress by punching press duct the refluence to turbofan duct, improve the propulsive performance of engine.Can find out from motion pattern, there is obvious low speed recirculating zone in flameholder rear.Stabilizer inner flow velocity on duty is less, is conducive to realize the igniting of super combustion chamber; Inside stretch radially and have the low speed recirculating zone that yardstick is larger after stabilizer and overhanging radially stabilizer, for biography flame and the flame stabilization of super combustion chamber provide advantage.
By method for numerical simulation, flow resistance characteristic of the present invention is studied.In Fig. 5, Article 1 is square lobe mixer outlet cross section perpendicular to the straight line of transverse axis, and Article 2 straight line vertical and transverse axis is flameholder trailing edge cross section.As seen from Figure 5, the flow resistance coefficient of right margin is all less than 2.2, and square lobe internal mixer, square lobed mixer lose larger to the dilution zone of flameholder trailing edge.
Under certain typicalness point, the combustion characteristics of super combustion chamber provided by the invention is carried out to numerical simulation.The calculating that adopts DPM model to carry out the calculating of mist of oil field and burn with EDC model, chemical reaction.Nozzle arrangements in super combustion chamber adopts simple nozzle model, and each injection diameter is 0.5mm, and initial oil droplet SMD is 50 μ m.Owing to can not simulate really the EVAP process of evaporation tubular type flameholder at FLUENT, therefore simplify for the fuel feeding of stabilizer on duty, adopt pneumatic nozzle fuel feeding and the SMD of initial oil droplet is made as to 20 μ m, the fuel oil atomization preferably that makes to enter stabilizer on duty, is conducive to start chemical reaction.Numerical simulation result shows, under the condition that is 1.53 at typicalness point excess air coefficient, the outlet mean temperature of super combustion chamber is 2026K, and efficiency of combustion is 96.4%.As seen from Figure 6, the flame evolution in super combustion chamber, first in formation high-temperature region, low regime, flameholder rear and produce initial flame, along with the increase of combustion zone length, it is large that high-temperature region area becomes, and burns to unofficial biography flame.As shown in Figure 7 and Figure 8, to super combustor exit, overhanging change groove width radially between flameholder flame be connected, Temperature Distribution is comparatively reasonable.
Claims (7)
1. the super combustion chamber of turbine base combined cycle engine, it is characterized in that: comprise flow splitter (1), rear variable area vent valve (2), water conservancy diversion tongue piece (3), square lobed mixer (4), center cone (6), be arranged on fueller on center cone (6) and flameholder, heat screen (9), super combustion chamber cylindrical shell (10) covers on outermost layer; Between described square lobed mixer (4) and flow splitter (1), be separated from each other, exist wheelbase from; Water conservancy diversion tongue piece (3) is fixed in runner, and is next to rear variable area vent valve (2) afterwards, is right against square lobed mixer (4) trough top with discrete shape.
2. the super combustion chamber of turbine base combined cycle engine according to claim 1, it is characterized in that: described flameholder mainly by evaporation tubular type flameholder (8), be arranged on evaporation tubular type flameholder (8) outer rim overhanging change groove width radially flameholder (11) and be arranged on inside evaporation tubular type flameholder (8) in stretch radially flameholder (12) and form, flameholder blockage ratio is 43.6%; Evaporation tubular type flameholder (8) comprises Fuel Injector Bar on duty (8-1), oil splasher (8-2), air entraining pipe (8-3), pre-gas inlet (8-4), fuel-rich mixed gas venthole (8-5), evaporation tube (8-6) and V-type groove (8-7); There is the angle of sweep of 45 ° ~ 60 ° with super combustion chamber axis in some overhanging change groove widths radially flameholder (11), evenly be fixed on V-type groove (8-7), and the groove width of locating near super combustion chamber cylindrical shell (10) is larger, the groove width of locating near V-type groove (8-7) is less; Inside stretch radially stabilizer (12) and be fixedly connected on center cone (6) tail end.
3. the super combustion chamber of turbine base combined cycle engine according to claim 2, is characterized in that: described fueller comprises I district Fuel Injector Bar (5), II district injection loop (7) and described Fuel Injector Bar on duty (8-1); I district Fuel Injector Bar (5) is positioned at square lobed mixer (4) outlet, and with just right in square lobed mixer (4) dividing plate.
4. the super combustion chamber of turbine base combined cycle engine according to claim 3, is characterized in that: described square lobed mixer (4) adopts up and down the lobe of the angle of flare such as not.
5. the super combustion chamber of turbine base combined cycle engine according to claim 4, it is characterized in that: the number of described water conservancy diversion tongue piece (3) is identical with the lobe number of square lobed mixer (4), its flow-deviation angle equates with lobed mixer (4) the trough place angle of flare.
6. the super combustion chamber of turbine base combined cycle engine according to claim 5, it is characterized in that: described center cone (6) surface is spheroid shape, and jointly completes the blending task of super combustion chamber with water conservancy diversion tongue piece (3) and square lobed mixer (4).
7. the super combustion chamber of turbine base combined cycle engine according to claim 6, it is characterized in that: described Ⅰ district Fuel Injector Bar (5) adopts circumferential side spray, II district injection loop (7) adopts radially side spray, and Fuel Injector Bar on duty (8-1) adopts radial spray mode.
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| CN110523962A (en) * | 2019-09-27 | 2019-12-03 | 安徽信息工程学院 | Spray furnace in casting ladle baking whirlpool |
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