CN102384489A - Small-sized annular combustion chamber with high-capacity heat intensity - Google Patents
Small-sized annular combustion chamber with high-capacity heat intensity Download PDFInfo
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- CN102384489A CN102384489A CN201110177636XA CN201110177636A CN102384489A CN 102384489 A CN102384489 A CN 102384489A CN 201110177636X A CN201110177636X A CN 201110177636XA CN 201110177636 A CN201110177636 A CN 201110177636A CN 102384489 A CN102384489 A CN 102384489A
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Abstract
The invention discloses a small-sized annular combustion chamber with high-capacity heat intensity, which comprises a combustion chamber casing, an oil supply component, an outer flame tube, an inner flame tube, a high-pressure turbine guider, an oil thrower wheel and an igniter, wherein the oil supply component is fixed on the combustion chamber casing; and the outer flame tube, the inner flame tube and the high-pressure turbine guider are fixedly connected with the combustion chamber casing. As an oil thrower wheel type baffling combustion chamber is adopted by the annular combustion chamber, and a radial combustion way is used, the axial size of the combustion chamber can be reduced, the size of the combustion chamber is reduced, and the heat capacity intensity of the combustion chamber can be effectively improved.
Description
Technical field
The present invention relates to Aero-Space Machine Design and manufacturing technology field, particularly a kind of small-size annular combustion chamber of high volumetric heat intensity.
Background technology
Volume rate of combustion is defined as the combustion chamber under unit pressure, the heat that the unit volume fuel combustion is per hour discharged, and it is the index of reaction chamber's structural compactness.Volumetric heat intensity is high, show that the needed combustion chamber volume of fuel of the same traffic of burning is little, so its size is little, and is in light weight.In Small Gas Turbine Engine, in order to reduce the combustion chamber size and to improve the baffling combustion chamber that its volumetric heat intensity adopts the band disc usually.In this combustion chamber, fuel oil is fed to engine spindle and flows to the disc that is contained on the main shaft, under the centrifugal action that main shaft rotates at a high speed, gets rid of in the combustion chamber through the radial hole on the handsome food tray.It can guarantee when fuel flow is minimum, to still have good atomizing, makes the combustion chamber in less volume, fully burn.
Yet the shortcoming of prior art is that current combustion chamber size and weight are bigger, can't satisfy the demand of miniaturization.In addition, volume rate of combustion is still lower, needs to improve.
Summary of the invention
The object of the invention is intended to solve at least one of above-mentioned technological deficiency, and special proposition solution combustion chamber size and weight are big, the defective that volumetric heat intensity is low.
The embodiment of the invention has proposed a kind of small-size annular combustion chamber of high volumetric heat intensity, comprising: combustion box; Be fixed on the fuel feeding assembly on the said combustion box, said fuel feeding assembly is provided with a plurality of nozzle openings; The outer burner inner liner that is fixedly connected with said combustion box, interior burner inner liner and high-pressure turbine guider; Wherein, The diameter of said outer burner inner liner is greater than the diameter of burner inner liner in said; The axial length of said outer burner inner liner is greater than the axial length of burner inner liner in said; And said outer burner inner liner comprises outer burner inner liner housing and antetheca assembly, is provided with a plurality of primary holes, a plurality of strip blending hole and a plurality of circular blending hole on the said outer burner inner liner housing successively, and said antetheca assembly upper edge circumferentially outwards is provided with the cooling holes and the tangential line of rabbet joint from the center of circle of said antetheca assembly successively; With the relative disc of said a plurality of nozzle openings; Said nozzle opening is sprayed onto fuel oil on the said disc; Wherein, said disc has a plurality of radially nozzle openings and said disc can rotate at a high speed fuel oil is got rid of into the burner inner liner that is limited said outer burner inner liner and interior burner inner liner so that said fuel oil is atomized; And igniter, said igniter is used for the fuel oil among the said burner inner liner is lighted a fire.
In one embodiment of the invention, the inlet of said high-pressure turbine guider is provided with hollow blade.
In one embodiment of the invention, said interior burner inner liner is a waveform.
In one embodiment of the invention, said interior burner inner liner is provided with a plurality of primary holes and a plurality of circular blending hole.
In one embodiment of the invention; When said toroidal combustion chamber is worked; Pressure-air is divided into three parts after getting into the combustion chamber through said combustion box; First gets into the primary zone in the said burner inner liner through the cooling holes on the antetheca assembly of said outer burner inner liner and the tangential line of rabbet joint; Second portion passes through the ring cavity that said high-pressure turbine guider hollow blade gets into said interior burner inner liner, and gets in the said burner inner liner through the primary holes of burner inner liner in said, and third part gets in the said burner inner liner through the primary holes on the housing of said outer burner inner liner, strip blending hole and circular blending hole.
In one embodiment of the invention, after the first of said pressure-air and second portion got into fuel oil after burner inner liner atomizes with said disc and carry out blending, said igniter was lighted a fire to fuel oil.
The small-size annular combustion chamber of the embodiment of the invention has the following advantages:
1, the embodiment of the invention adopts disc that fuel oil is atomized, thereby has guaranteed the uniformity of fuel-oil atmozation, and adopts the mode of the outer fuel feeding of axle, efficiently solves the many problems of an interior fuel system rotatory sealing place oil leakage fault.
2, in embodiments of the present invention, outer burner inner liner radial diameter is big, and axial length is short, thereby the radial combustion mode can be adopted in the combustion chamber, has reduced the volume of combustion chamber, can effectively improve volume rate of combustion.
3, the tangential translot of the antetheca assembly of outer burner inner liner and interior burner inner liner primary holes can form a plurality of little recirculating zones in burner inner liner, make the fully smooth combustion of the combustion zone of fuel oil in burner inner liner.
Aspect that the present invention adds and advantage part in the following description provide, and part will become obviously from the following description, or recognize through practice of the present invention.
Description of drawings
Above-mentioned and/or additional aspect of the present invention and advantage are from obviously with easily understanding becoming the description of embodiment below in conjunction with accompanying drawing, wherein:
Fig. 1 is the small-size annular chamber structure figure of the high volumetric heat intensity of the embodiment of the invention;
Fig. 2 is the structure chart of the outer burner inner liner of the embodiment of the invention;
Fig. 3 is the structure chart of the interior burner inner liner of the embodiment of the invention.
The specific embodiment
Describe embodiments of the invention below in detail, the example of said embodiment is shown in the drawings, and wherein identical from start to finish or similar label is represented identical or similar elements or the element with identical or similar functions.Be exemplary through the embodiment that is described with reference to the drawings below, only be used to explain the present invention, and can not be interpreted as limitation of the present invention.
As shown in Figure 1, be the small-size annular chamber structure figure of the high volumetric heat intensity of the embodiment of the invention.The small-size annular combustion chamber of this high volumetric heat intensity comprises combustion box 1, disc 2, fuel feeding assembly 3, outer burner inner liner 4, interior burner inner liner 5, high-pressure turbine guider 6 and igniter 7.Wherein, adopt the mode of the outer fuel feeding of axle, the fuel feeding assembly is fixed on the combustion box 1 through screw, and the outlet of fuel feeding assembly 3 is provided with a plurality of nozzle openings, for example 10-15 nozzle opening.Disc 2 is fixed together with engine high pressure axle (not shown), and along with high-pressure shaft is rotated at a high speed.In this embodiment; Disc 2 is relative with a plurality of nozzle openings of fuel feeding assembly 3; Nozzle opening through fuel feeding assembly 3 can be sprayed onto fuel oil on the disc 2; Wherein, disc 2 has a plurality of radially nozzle openings and disc 2 and can rotate at a high speed fuel oil is got rid of into the burner inner liner that is limited outer burner inner liner 4 and interior burner inner liner 5 so that fuel oil is atomized.Thereby the disc of fuel feeding assembly 3 and rotation has at a high speed just been formed the fuel-oil atmozation system of combustion chamber; After the nozzle opening of fuel oil through fuel feeding assembly 3 is sprayed onto on the disc 2; Disc 2 drives fuel oils and does high speed rotary motion, and it is got rid of among the combustion chamber through nozzle opening radially with speed greatly.Thereby guaranteed under the minimum situation of amount of fuel, still can guarantee good atomizing effect, and made fuel oil in the combustion chamber, circumferentially evenly distribute.
In an embodiment of the present invention, combustion box 1, outer burner inner liner 4, interior burner inner liner 5 are fixed together through screw and high-pressure turbine guider 6.Igniter 7 is used for the fuel oil among the burner inner liner is lighted a fire.Shown in Fig. 2 and 3, be respectively the structure chart of outer burner inner liner of the embodiment of the invention and interior burner inner liner.Wherein, the diameter of outer burner inner liner 4 is greater than the diameter of interior burner inner liner 5, and the axial length of outer burner inner liner 4 is greater than the axial length of interior burner inner liner 5, and outer burner inner liner 4 comprises outer burner inner liner housing 41 and antetheca assembly 42.Wherein, be the primary zone of burning near antetheca assembly 42.This toroidal combustion chamber adopts the baffling combustion chamber of disc formula, adopts the mode of radial combustion, thereby can reduce the axial dimension of combustion chamber, dwindles combustion chamber volume, effectively improves the volumetric heat intensity of combustion chamber.
As shown in Figure 2, burner inner liner housing 41 is provided with a plurality of primary holes 411, a plurality of strip blending hole 412 and a plurality of circular blending hole 413 outside.Wherein, primary holes 411, strip blending hole 412 are identical with the number of circular blending hole 413.The wall of burner inner liner 5 can separate combustion zone in the burner inner liner and dilution zone effectively, thereby further improve the volumetric heat intensity of combustion chamber in strip blending hole 412 its penetration depths ability ways in the embodiment of the invention.
Circumferentially outwards be provided with the cooling holes 421 and the tangential line of rabbet joint 422 successively from the center of circle of said antetheca assembly in antetheca assembly 42 upper edges.Cooling holes 421 can be cooled off the burner inner liner wall in primary zone effectively.The tangential line of rabbet joint 422 that air communication is crossed antetheca assembly 42 can form the jet of rotation, makes to constitute many little recirculating zones in the space between antetheca assembly 42 and the interior burner inner liner 5, makes fuel oil abundant stable burning in this zone.
As shown in Figure 3, interior burner inner liner 5 undulates distribute, and on interior burner inner liner 5, are provided with primary holes 51 and circular blending hole 52.The inlet of high-pressure turbine guider 6 is provided with hollow blade; In the ring cavity of air through burner inner liner 5 in the hollow blade entering of high-pressure turbine guider 6 of combustion box 1 entering, enter in the burner inner liner through primary holes on the interior burner inner liner 5 51 and circular blending hole 52 again.
Work as engine operation; When being toroidal combustion chamber work; Pressure-air is through being divided into three parts after the combustion box 1 entering combustion chamber; First then inwardly changes 90 ° forward earlier, through the primary zone in cooling holes on the antetheca assembly 42 of outer burner inner liner 4 421 and the tangential line of rabbet joint 422 entering burner inner liners; Second portion is through the ring cavity of burner inner liner 5 in the hollow blade entering of high-pressure turbine guider 6, and the primary holes through interior burner inner liner 5 enters in the burner inner liner again; Third part gets in the burner inner liner through the primary holes 411 on the outer burner inner liner housing 41, strip blending hole 412 and circular blending hole 413.After the first of pressure-air and second portion got into fuel oil after burner inner liner atomizes with disc 2 and carry out blending, 7 pairs of fuel oils of igniter were lighted a fire and are taken fire.The mixed gaseous mixture of fuel oil and two parts air-flow radially outward earlier; Then axially flow backward again; In flow process, accomplish all burnings; Then the third part air-flow enters into burner inner liner from primary holes 411, strip blending hole 412 and circular blending hole 413 on the outer burner inner liner housing 4, with combustion gas mixing, accomplishes blending.
The small-size annular combustion chamber of the embodiment of the invention has the following advantages:
1, the embodiment of the invention adopts disc that fuel oil is atomized, thereby has guaranteed the uniformity of fuel-oil atmozation, and adopts the mode of the outer fuel feeding of axle, efficiently solves the many problems of an interior fuel system rotatory sealing place oil leakage fault.
2, in embodiments of the present invention, outer burner inner liner radial diameter is big, and axial length is short, thereby the radial combustion mode can be adopted in the combustion chamber, has reduced the volume of combustion chamber, can effectively improve volume rate of combustion.
3, the tangential translot of the antetheca assembly of outer burner inner liner and interior burner inner liner primary holes can form a plurality of little recirculating zones in burner inner liner, make the fully smooth combustion of the combustion zone of fuel oil in burner inner liner.
In the description of this specification, the description of reference term " embodiment ", " some embodiment ", " example ", " concrete example " or " some examples " etc. means the concrete characteristic, structure, material or the characteristics that combine this embodiment or example to describe and is contained at least one embodiment of the present invention or the example.In this manual, the schematic statement to above-mentioned term not necessarily refers to identical embodiment or example.And concrete characteristic, structure, material or the characteristics of description can combine with suitable manner in any one or more embodiment or example.
Although illustrated and described embodiments of the invention; For those of ordinary skill in the art; Be appreciated that under the situation that does not break away from principle of the present invention and spirit and can carry out multiple variation, modification, replacement and modification that scope of the present invention is accompanying claims and be equal to and limit to these embodiment.
Claims (6)
1. the small-size annular combustion chamber of a high volumetric heat intensity is characterized in that, comprising:
Combustion box;
Be fixed on the fuel feeding assembly on the said combustion box, said fuel feeding assembly is provided with a plurality of nozzle openings;
The outer burner inner liner that is fixedly connected with said combustion box, interior burner inner liner and high-pressure turbine guider; Wherein, The diameter of said outer burner inner liner is greater than the diameter of burner inner liner in said; The axial length of said outer burner inner liner is greater than the axial length of burner inner liner in said; And said outer burner inner liner comprises outer burner inner liner housing and antetheca assembly, and said outer burner inner liner housing is provided with a plurality of primary holes, a plurality of strip blending hole and a plurality of circular blending hole, and said antetheca assembly upper edge circumferentially outwards is provided with the cooling holes and the tangential line of rabbet joint from the center of circle of said antetheca assembly successively;
With the relative disc of said a plurality of nozzle openings; Said nozzle opening is sprayed onto fuel oil on the said disc; Wherein, said disc has a plurality of radially nozzle openings and said disc can rotate at a high speed fuel oil is got rid of into the burner inner liner that is limited said outer burner inner liner and interior burner inner liner so that said fuel oil is atomized; With
Igniter, said igniter are used for the fuel oil among the said burner inner liner is lighted a fire.
2. the small-size annular combustion chamber of high volumetric heat intensity as claimed in claim 2 is characterized in that, the inlet of said high-pressure turbine guider is provided with hollow blade.
3. the small-size annular combustion chamber of high volumetric heat intensity as claimed in claim 1 is characterized in that, said interior burner inner liner is a waveform.
4. the small-size annular combustion chamber of high volumetric heat intensity as claimed in claim 3 is characterized in that, said interior burner inner liner is provided with a plurality of primary holes and a plurality of circular blending hole.
5. the small-size annular combustion chamber of high volumetric heat intensity as claimed in claim 3; It is characterized in that; When said toroidal combustion chamber is worked; Pressure-air is divided into three parts after getting into the combustion chamber through said combustion box; First gets into the primary zone in the said burner inner liner through the cooling holes on the antetheca assembly of said outer burner inner liner and the tangential line of rabbet joint; Second portion passes through the ring cavity that said high-pressure turbine guider hollow blade gets into said interior burner inner liner, and gets in the said burner inner liner through the primary holes of burner inner liner in said, and third part gets in the said burner inner liner through the primary holes on the housing of said outer burner inner liner, strip blending hole and circular blending hole.
6. the small-size annular combustion chamber of high volumetric heat intensity as claimed in claim 5; It is characterized in that; After the first of said pressure-air and second portion got into fuel oil after burner inner liner atomizes with said disc and carry out blending, said igniter was lighted a fire to fuel oil.
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| CN201110177636.XA CN102384489B (en) | 2011-06-28 | 2011-06-28 | Small-sized annular combustion chamber with high-capacity heat intensity |
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| CN201110177636.XA CN102384489B (en) | 2011-06-28 | 2011-06-28 | Small-sized annular combustion chamber with high-capacity heat intensity |
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| CN102384489B CN102384489B (en) | 2014-01-22 |
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Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104180398A (en) * | 2014-08-24 | 2014-12-03 | 武汉英康汇通电气有限公司 | Annular combustor |
| CN104236917A (en) * | 2014-09-05 | 2014-12-24 | 北京动力机械研究所 | Full-ring micro-size backflow combustor tester |
| CN105042637A (en) * | 2015-07-09 | 2015-11-11 | 中国航空工业集团公司沈阳发动机设计研究所 | Combustion chamber |
| CN105114983A (en) * | 2015-09-24 | 2015-12-02 | 北京动力机械研究所 | Omega-shaped flame tube |
| CN106196170A (en) * | 2016-07-21 | 2016-12-07 | 中国航空动力机械研究所 | Centrifugal oil swirling atomization structure |
| CN106351747A (en) * | 2016-11-21 | 2017-01-25 | 中国航空动力机械研究所 | Fuel supply system and fuel supply method for small-power gas-turbine engine |
| CN106524225A (en) * | 2016-10-31 | 2017-03-22 | 北京动力机械研究所 | Flame tube suitable for three-vortex-system structure combustion of advanced low-pollution turbine engine |
| CN108151069A (en) * | 2017-11-30 | 2018-06-12 | 北京动力机械研究所 | A kind of primary zone Radial Flow combustion chamber and oil gas mixing method |
| CN108167864A (en) * | 2017-11-20 | 2018-06-15 | 北京动力机械研究所 | Burner inner liner and high-pressure turbine guider integral structure |
| CN112524640A (en) * | 2020-11-30 | 2021-03-19 | 北京动力机械研究所 | Secondary distribution oil supply structure |
| CN115143491A (en) * | 2022-06-06 | 2022-10-04 | 中科航星科技有限公司 | Be suitable for disc combustion chamber inner ring flame tube cooling module |
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Cited By (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104180398A (en) * | 2014-08-24 | 2014-12-03 | 武汉英康汇通电气有限公司 | Annular combustor |
| CN104236917A (en) * | 2014-09-05 | 2014-12-24 | 北京动力机械研究所 | Full-ring micro-size backflow combustor tester |
| CN104236917B (en) * | 2014-09-05 | 2017-02-08 | 北京动力机械研究所 | Full-ring micro-size backflow combustor tester |
| CN105042637A (en) * | 2015-07-09 | 2015-11-11 | 中国航空工业集团公司沈阳发动机设计研究所 | Combustion chamber |
| CN105114983A (en) * | 2015-09-24 | 2015-12-02 | 北京动力机械研究所 | Omega-shaped flame tube |
| CN106196170B (en) * | 2016-07-21 | 2018-08-31 | 中国航空动力机械研究所 | Centrifugal oil swirling atomization structure |
| CN106196170A (en) * | 2016-07-21 | 2016-12-07 | 中国航空动力机械研究所 | Centrifugal oil swirling atomization structure |
| CN106524225B (en) * | 2016-10-31 | 2019-01-15 | 北京动力机械研究所 | The three vortex system tissue burned flame cylinders suitable for advanced low pollution turbogenerator |
| CN106524225A (en) * | 2016-10-31 | 2017-03-22 | 北京动力机械研究所 | Flame tube suitable for three-vortex-system structure combustion of advanced low-pollution turbine engine |
| CN106351747B (en) * | 2016-11-21 | 2018-03-09 | 中国航空动力机械研究所 | A kind of fuel oil supply system and method for small-power gas-turbine unit |
| CN106351747A (en) * | 2016-11-21 | 2017-01-25 | 中国航空动力机械研究所 | Fuel supply system and fuel supply method for small-power gas-turbine engine |
| CN108167864A (en) * | 2017-11-20 | 2018-06-15 | 北京动力机械研究所 | Burner inner liner and high-pressure turbine guider integral structure |
| CN108151069A (en) * | 2017-11-30 | 2018-06-12 | 北京动力机械研究所 | A kind of primary zone Radial Flow combustion chamber and oil gas mixing method |
| CN108151069B (en) * | 2017-11-30 | 2020-03-31 | 北京动力机械研究所 | Main combustion zone radial flow combustion chamber and oil-gas mixing method |
| CN112524640A (en) * | 2020-11-30 | 2021-03-19 | 北京动力机械研究所 | Secondary distribution oil supply structure |
| CN115143491A (en) * | 2022-06-06 | 2022-10-04 | 中科航星科技有限公司 | Be suitable for disc combustion chamber inner ring flame tube cooling module |
| CN115143491B (en) * | 2022-06-06 | 2024-04-12 | 中科航星科技股份有限公司 | Be suitable for oil slinger combustor inner ring flame tube cooling module |
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