CN103115381B - Cylinder wall structure of flame tube - Google Patents
Cylinder wall structure of flame tube Download PDFInfo
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- CN103115381B CN103115381B CN201110365084.5A CN201110365084A CN103115381B CN 103115381 B CN103115381 B CN 103115381B CN 201110365084 A CN201110365084 A CN 201110365084A CN 103115381 B CN103115381 B CN 103115381B
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Abstract
Provided is a cylinder wall structure of a flame tube. The cylinder wall structure of the flame tube comprises an outer wall portion which is ring-shaped, wherein a first array hole is formed in the outer wall portion; inner wall portion which is ring-shaped, the inner wall portion and the outer wall portion commonly limit a ring-shaped empty chamber, a second array hole is formed in the inner wall portion and a protruding table array which extends to the outer wall portion is formed in the inner wall portion; wherein the first array hole reverses flow direction of cooling gas and extends obliquely, the second array hole and the first array hole are placed in a staggered mode and are consequent to the flow direction of the cooling gas and extend obliquely, and the first array hole, the second array hole and the protruding table array are placed as following: when the cooling gas passes through the outer surface of the outer wall portion, a part of the cooling gas enters the ring-shaped empty chamber through the first array hole, and impacts on the rim of the protruding table array, and then outflows from the second array hole. The cylinder wall structure of the flame tube can enhance heat exchange.
Description
Technical field
The present invention relates to burner inner liner, particularly relate to the Cylinder wall structure of burner inner liner.
Background technology
As everyone knows, gas turbine both extensive uses in power field, are also widely used in driving jet plane.In the gas turbine, the mixture of air and fuel is lighted in a combustion chamber, and the red-hot air-flow produced by burning expands in turbine space, thermal current contacts with the structure comprising each guide vane and turbo blade there, and the turbo blade that promotion is configured on axle rotates, therefore axle itself rotates.
For the gas turbine of aircraft, combustion chamber is by compressor pressure-air out and fuel mix and carries out the device that burns.In combustion chamber, the chemical energy in fuel (as aviation kerosine) changes heat energy into through burning, and gas temperature is increased greatly.The high temperature flowed out by combustion chamber, high pressure (basic identical with blower outlet pressure) combustion gas, have very high energy, in order to expansion working in the turbine behind combustion chamber and jet pipe.Burner inner liner is the indispensable core component in combustion chamber of the engine of aircraft, generally be made up of high-temperature alloy material, the portion of air that its role is to fuel and compressor to send here carries out active combustion in burner inner liner, is its expansion work preparatory condition in gas turbine.For toroidal combustion chamber, burner inner liner is generally made up of two concentric circles housings around engine axis, and form an annular cavity, inside and outside housing is called the inside and outside shell of burner inner liner.Burner inner liner shell by an annular outer casing institute around, an annular interior casing is also housed inside burner inner liner inner casing, and in other words, inside and outside casing defining therebetween burner inner liner.
Because the burning of the mixture of air and fuel causes burner inner liner to stand very high temperature, and along with the continuous lifting required low stain, reduce for the air that cools, new challenge is proposed to the structure of burner inner liner and cooling scheme thereof.
As shown in Figure 1, it illustrates a kind of structure of burner inner liner 10 of prior art, this burner inner liner 10 has casing 1, outer burner inner liner 2, flame cylinder 3 (the inside and outside distance by distance engine axis) and head of combustion chamber 4.Outer burner inner liner 2 and flame cylinder 3 form combustion chamber 5, it are furnished with air film hole 6 and blending hole 7.Flame cylindrical shell adopts overall structure and and forms diffuser 8 between casing 1.In actual motion, a part of pressure-air directly enters in combustion chamber 5, and another part pressure-air can flow through diffuser 8 and to enter in combustion chamber 5 through air film hole 6 and blending hole 7 again thus realize the cooling to flame cylindrical shell.Because this flame cylindrical shell bears alternation thermal force, occur serious low-cycle fatigue crackle possibly at exhaust group section axial and circumferential, and its recoverability is poor, can not meet the more and more higher requirement of aero-engine.
In the layout of cooling scheme, more representational is GE (GeneralElectric, General Electric) the impact aerating film cooling of company and the reverse concurrent flow wing wall of PW (Pratt & Whitney, Alexandre Desplat Whitney) company cool.But these above-mentioned two kinds of common Problems existing of structure are that cooling structure is various and processing technology complicated.
Authorization Notice No. is that the Chinese invention patent of CN 101526228B discloses a kind of reentry type compound cooling structure.This cooling structure mainly comprises end wall, lateral wall, madial wall, midfeather is provided with between lateral wall and madial wall, lateral wall, midfeather and madial wall form three layers of wall construction, and by end wall by madial wall and lateral wall closed at both ends, midfeather rear end is connected with aft bulkhead; The back segment of lateral wall is provided with impact opening, and cooling-air enters this cooling structure at the back segment of lateral wall with the form of impact air-flow; The cooling-air groove of certain intervals is set between the front end of midfeather and end wall, between midfeather and lateral wall, forms the upper cooling duct of certain intervals, between midfeather and madial wall, form the lower cooling duct of certain intervals; The lateral surface of midfeather is furnished with lacuna shape fourth born of the same parents hole; Madial wall is effusion wall hole wall cooling structure, adopts reducing and expansion air film hole, and refrigerating gas is first shrink the type of flow expanded afterwards in hole.Although this structure has good cooling effect, but because it has set up midfeather, cause flow losses comparatively large thus the pressure loss is comparatively large so cold gas flow path is longer, and its complex structure, weight are comparatively large, in addition, it processes also more complicated.
Summary of the invention
A Cylinder wall structure for burner inner liner, it comprises: outer wall section, ringwise, it is furnished with the first array hole; Inner wall section, ringwise, limits toroidal cavity jointly with described outer wall section; Described inner wall section be furnished with the second array hole and be formed with the mesa array extended to described outer wall section; Wherein, the reverse flow direction in cold gas of described first array hole extends obliquely, described second array hole and described first array hole are arranged alternately and forward extend obliquely in the flow direction of cold gas, described first array hole, the second array hole and mesa array are arranged to when cold gas is through the outer surface of described outer wall section, part cold gas enters described toroidal cavity through described first array hole, and impact the edge of described mesa array, then flow out from described second array hole.Wherein, when described cold gas is passed from described Cylinder wall structure, its running orbit is roughly S shape.
More preferably, described outer wall section is one, and described inner wall section is that multiple unit is formed.
More preferably, described outer wall section is integrated, described inner wall section is made up of multiple inwall unit, and the inner surface of described outer wall section and the outer surface of described inwall unit are relatively provided with grab respectively to be hooked on described outer wall section by described inwall unit.
More preferably, described inwall unit connects into described inner wall section by bridging arrangement, and form overlap joint gap between described bridging arrangement, flame-proof sealing material is attached to described overlap joint gap location.
Optionally, the boss in described mesa array is rhombus or rectangle.
Optionally, described boss is that smart type casting moulding or precision milling are formed.
More preferably, described second array hole is elliptical aperture, and the equivalent diameter of elliptical aperture is 0.4-1.5mm.
More preferably, the inner surface of described inner wall section is coated with thermal barrier coating.
Selectively, described outer wall section and described inner wall section are made up of high-temperature alloy material, wherein, described inner wall section be by without surplus hot investment casting and two ends grinding form.
More preferably, the bearing of trend of described first array hole and the flow direction of described cold gas are the inclination angle of 20 ° ~ 45 °.
More preferably, the bearing of trend of described second array hole and the flow direction of described cold gas are the inclination angle of-70 ° ~-20 °.
Accompanying drawing explanation
Fig. 1 schematically shows the structure of a kind of burner inner liner of the prior art;
Fig. 2 schematically show of the present invention a kind of preferred embodiment in the local structural graph of Cylinder wall structure of burner inner liner;
Fig. 3 schematically show of the present invention a kind of preferred embodiment in the part sectioned view of Cylinder wall structure of burner inner liner;
Fig. 4 schematically show of the present invention a kind of preferred embodiment in the top view of inner wall section of Cylinder wall structure of burner inner liner;
Fig. 5 schematically show of the present invention a kind of preferred embodiment in the upward view of inner wall section of Cylinder wall structure of burner inner liner;
Fig. 6 schematically show of the present invention a kind of preferred embodiment in the overlap joint of cell block of Cylinder wall structure of burner inner liner and hooking structure.
Detailed description of the invention
As described in the background section, burner inner liner generally all has outer burner inner liner (or claiming burner inner liner shell) and flame cylinder (or claiming burner inner liner inner casing), and combustion chamber is formed at the centre of outer burner inner liner and flame cylinder.It should be noted that at this, the Cylinder wall structure of burner inner liner hereinafter described does not refer to the structure of the whole burner inner liner with outer burner inner liner and flame cylinder, and refers to the structure of outer burner inner liner or the structure of flame cylinder itself.More preferably, the Cylinder wall structure of burner inner liner of the present invention can be applied to flame cylinder and outer burner inner liner simultaneously.In addition, the inside and outside differentiation of so-called inner wall section and outer wall section is the distance according to distance center, combustion chamber, and specifically, the wall portion near center, combustion chamber is called inner wall section, and the wall portion away from center, combustion chamber is called outer wall section.
As shown in Figure 2, the Cylinder wall structure 100 of burner inner liner is divided into two-layer.One deck of Cylinder wall structure 100 is outer wall section 102, and substantially ringwise, its material is more preferably high temperature alloy; Another layer of Cylinder wall structure is inner wall section 104, and substantially ringwise, its material is more preferably high temperature alloy, with such as Near net shape hot investment casting and two ends grinding form; Outer wall section 102 and inner wall section 104 are situated between and form cavity 106.
In preferrred embodiment of the present invention as shown in the figure, burner inner liner is made up of the outer burner inner liner of annular and annular flame cylinder, and wherein, outer burner inner liner and flame cylinder all have the Cylinder wall structure 100 of the double-walled that hereafter will describe in detail.Wherein, the Cylinder wall structure 100 of double-walled is made up of outer wall section 102 and inner wall section 104.Particularly, outer wall section 102 is integral type structure, and inner wall section 104 is fraction block structure.More specifically, inner wall section 104 is divided into three sections in the axial direction, and wherein, for outer burner inner liner, the inner wall section 104 of outer burner inner liner is made up of 20 cell blocks in the circumferential; For flame cylinder, the inner wall section 104 of flame cylinder is made up of 15 cell blocks in circumference; That is, for whole burner inner liner, the inner wall section 104 that the outer wall section 102 of an integral type and 60 cell blocks are formed defines outer burner inner liner, and the inner wall section 104 that the outer wall section 102 of an integral type and 45 cell blocks are formed defines flame cylinder.。Those skilled in the art is easy to the section of being appreciated that division and cell block division is not limited thereto.Like this, lap one another in the axial direction between cell block and form " tile " type layout together.More specifically, as shown in Figure 6, each cell block of inner wall section 104 all has " Z " character form structure at circumferential and axial, bridging type is adopted to connect between each cell block, thus forming its one end by the support of adjacent cell block thereon, its other end is supported in the load-carrying construction on adjacent cell block.Preferably, the place of lapping one another 118 can be attached to a small amount of flame-proof sealing material to reduce the gas leakage of lap-joint.Outer wall section 102 and inner wall section 104 all has the hook 120 that corresponds to each other to be suspended on outer wall section 102 by each cell block of inner wall section 104.Like this, by the hook 120 that " Z " character form structure of inner wall section 104 and outer wall section 102 and inner wall section 104 correspond to each other, outer wall section 102 and inner wall section 104 just combined as a whole.All leave a small amount of gap between the hook 120 of mutual hook and between the mutual lap-joint 118 of " Z " character form structure, thus allow inner wall section 104 in axis, circumference and radial direction, all can have the leeway of a small amount of free wxpansion.
With reference to figure 3, outer wall section 102 uniform porose 108, defines the array in hole, preferably, in order to realize preferably impact characteristics, the airflow direction 110 that this hole 108 is flow through on the direction extended from inner wall section 104 to outer wall section 102 and from outer wall section 102 is in a sharp angle.More preferably, this sharp angle is 20 ° ~ 45 °.As long as be appreciated that hole 108 is arranged to reversely to extend obliquely in airflow direction 110.
Simultaneously with reference to figure 4 and Fig. 5, inner wall section 104 uniform porose 112, defines the array in hole, more preferably, this hole 112 to offer direction contrary with the direction in the hole 108 of outer wall section 102.As long as be appreciated that hole 112 is arranged to forward extend obliquely in airflow direction 110.Inner wall section 104 is also provided with boss 114 equably on the side towards outer wall section 102, and this boss 114 is provided so that the such as bight, an edge of boss 114 just corresponds to hole 108 thus makes the impact air-flow through via hole 108 can impact the edge (such as bight) of this boss 114.Like this, multiple boss 114 defines guiding gutter 116.Wherein, this boss 114 is more preferably rhombus.Be appreciated that this some holes 112 can form with such as electric spark or Laser Processing, these boss 114 also can be rectangle and or precision milling can be adopted to be formed via smart type casting moulding.More preferably, the angle of offering in hole 112 is-70 ° ~-20 °.In preferably embodiment of the present invention, this some holes 112 is elliptical aperture, and the equivalent diameter of ellipse is 0.4-1.5mm.
More preferably, the hole 108 on outer wall section 102 and hole 112 one_to_one corresponding in inner wall section 104 and interlaced arrangement.
Hot side surface sprays thermal barrier coating thus forms uniform air film protective layer.
The cooling procedure of the outer burner inner liner of the Cylinder wall structure formation of this burner inner liner is as described below:
The flow direction of high-temperature fuel gas that Reference numeral 110,122 represents the cold gas that flows through at outer wall section 102 outer surface respectively and flows through at the inner surface of inner wall section 104, when in cooling procedure, cold gas is passed from Cylinder wall structure, its travel track is roughly S shape, as shown in Reference numeral 124.Air flows into cavity 106 by the hole 108 that outer wall section 102 is arranged; impinging cooling boss 114; flow in guiding gutter 116 after air dispersion; hole 112 again in inner wall section 104 enters into the combustion chamber between outer burner inner liner and flame cylinder, and then forms uniform air film layer in the inner side of inner wall section 104 thus protect (or claiming hot side) inside inner wall section.
The combination of the present invention's application reverse impact-convection current-disperse (containing gaseous film control) three kinds of types of cooling, at least has the following advantages:
One, because outer wall section 102 on be evenly equipped with for cooling the circulation of vital energy in the wrong direction to impact hole 108, and hole 112 interlaced arrangement uniform in this hole 108 and inner wall section 104, so the forward position of Fast Cooling air-flow meeting reverse impact boss 114, then air-flow carries out heat convection after the dispersion of boss 114 forward position between guiding gutter 116.
Two, the interlaced arrangement mode in hole 108 and hole 112 makes cooling blast enter combustion chamber along serpentine path, adds air-flow traveling distance and time, thus reaches better cooling effect; This interlaced arrangement mode also makes cooling blast alternately shrink and expand, and increases flow perturbation, and then strengthens heat exchange.
Three, owing to being formed with guiding gutter 116 with the surface (can be described as cold side surface) of the inner wall section 104 faced by outer wall section 102, make the cooling structure of surface area considerably beyond routine of inner wall section 104, increase flow perturbation simultaneously, thus fully improve Convective heat tranfer cooling effect.
Four, link up with 120 to be connected with the bolt that " Z " shape bridging arrangement replaces routine, inner wall section 104 can be allowed to have a small amount of free wxpansion, and circumferential compartment of terrain layout hook 120 effectively can reduce the weight of burner inner liner.
Five, the thermal barrier coating of inner wall section 104 can form uniform air film protective layer thus can greatly reduce the heat convection between the inner surface (hot side surface) of hot combustion gas and inner wall section 104.
In order to verify heat transfer effect of the present invention, have selected two kinds of operating condition parameters, carry out three-dimensional CFD fluid and structural simulation to conventional chilling structure and cooling result of the present invention respectively, result of calculation sees the following form 1.
| Wall surface temperature (K) | Operating mode 1 | Operating mode 2 |
| Conventional cooling structure | 1157.1 | 1124.6 |
| Cooling structure of the present invention | 1142.7 | 1095.6 |
As can be seen from Table 1, utilize the burner inner liner of cooling structure of the present invention to compare with conventional burner inner liner, under two states, reduce 14.4K and 29K respectively, heat-transfer effect improves obviously.
Although foregoing description to be contrasted detailed description to the present invention, these are just illustrative to the present invention, instead of limitation of the present invention, and any innovation and creation do not exceeded in connotation of the present invention, all fall within the scope of protection of the present invention.
Claims (13)
1. a Cylinder wall structure for burner inner liner, it comprises:
Outer wall section, ringwise, it is furnished with the first array hole;
Inner wall section, ringwise, limits toroidal cavity jointly with described outer wall section, described inner wall section is furnished with the second array hole and is formed with the mesa array extended to described outer wall section;
Wherein, the reverse flow direction in cold gas of described first array hole extends obliquely, described second array hole and described first array hole are arranged alternately and forward extend obliquely in the flow direction of cold gas, described first array hole, described second array hole and described mesa array are arranged to when cold gas is through the outer surface of described outer wall section, part cold gas enters described toroidal cavity through described first array hole, and impact the edge of described mesa array, then flow out from described second array hole.
2. Cylinder wall structure according to claim 1, wherein, when described cold gas is passed from described Cylinder wall structure, its running orbit is roughly S shape.
3. Cylinder wall structure according to claim 1, wherein, described outer wall section is integrated, and described inner wall section is that multiple unit is formed.
4. Cylinder wall structure according to claim 1, wherein, described outer wall section is one, described inner wall section is made up of multiple inwall unit, and the inner surface of described outer wall section and the outer surface of described inwall unit are relatively provided with grab respectively to be hooked on described outer wall section by described inwall unit.
5. Cylinder wall structure according to claim 4, wherein, described inwall unit connects into described inner wall section by bridging arrangement, and form overlap joint gap between described bridging arrangement, flame-proof sealing material is attached to described overlap joint gap location.
6. the Cylinder wall structure according to any one of claim 1-5, wherein, the boss in described mesa array is rhombus or rectangle.
7. Cylinder wall structure according to claim 6, wherein, described boss is that smart type casting moulding or precision milling are formed.
8. the Cylinder wall structure according to any one of claim 1-7, wherein, described second array hole is elliptical aperture, and the equivalent diameter of elliptical aperture is 0.4-1.5mm.
9. the Cylinder wall structure according to any one of claim 1-8, wherein, the inner surface of described inner wall section is coated with thermal barrier coating.
10. Cylinder wall structure according to claim 1, wherein, described outer wall section and described inner wall section are made up of high-temperature alloy material, wherein, described inner wall section be by without surplus hot investment casting and two ends grinding form.
11. Cylinder wall structures according to any one of claim 1-10, wherein, the bearing of trend of described first array hole and the flow direction of described cold gas are the inclination angle of 20 ° ~ 45 °.
12. Cylinder wall structures according to any one of claim 1-11, wherein, the bearing of trend of described second array hole and the flow direction of described cold gas are in the inclination angle of-70 ° ~-20 °.
13. 1 kinds of burner inner liners, it has the Cylinder wall structure as described in any one of claim 1-12.
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| CN201110365084.5A CN103115381B (en) | 2011-11-17 | 2011-11-17 | Cylinder wall structure of flame tube |
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| CN201110365084.5A CN103115381B (en) | 2011-11-17 | 2011-11-17 | Cylinder wall structure of flame tube |
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| CN103115381B true CN103115381B (en) | 2015-04-01 |
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Families Citing this family (10)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN105222158B (en) * | 2014-06-30 | 2018-04-13 | 中国航发商用航空发动机有限责任公司 | Floating pad and combustion chamber flame drum |
| DE102014214981B3 (en) * | 2014-07-30 | 2015-12-24 | Siemens Aktiengesellschaft | Side-coated heat shield element with impingement cooling on open spaces |
| CN105276620B (en) * | 2015-06-26 | 2018-02-13 | 中航空天发动机研究院有限公司 | A kind of aeroengine combustor buring room burner inner liner wall compound cooling structure |
| CN106482133B (en) * | 2016-12-12 | 2019-03-05 | 深圳智慧能源技术有限公司 | The torch of cooling air is provided by gas source energy |
| CN109340826A (en) * | 2018-09-25 | 2019-02-15 | 西北工业大学 | A kind of flame combustion chamber tube wall surface two-layer compound cooling structure |
| CN111059575B (en) * | 2018-10-16 | 2022-05-10 | 中发天信(北京)航空发动机科技股份有限公司 | Turbojet engine flame tube shell |
| CN110081466A (en) * | 2019-01-18 | 2019-08-02 | 西北工业大学 | A kind of burner inner liner wall structure cooling using microchannel |
| CN110925791A (en) * | 2019-11-06 | 2020-03-27 | 西北工业大学 | Double-wall impact/Y-shaped multi-inclined-hole-wall composite cooling type combustion chamber flame tube wall surface structure |
| CN111365734A (en) * | 2020-03-25 | 2020-07-03 | 中国船舶重工集团公司第七0三研究所 | Mixed-grading ultra-low-emission flame tube |
| CN112228903B (en) * | 2020-09-18 | 2022-07-01 | 西北工业大学 | Three-channel type combustion chamber flame tube wall surface structure with longitudinal vortex generator |
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