CN105423344B - A kind of flame tube structure of ground combustion machine combustion chamber - Google Patents
A kind of flame tube structure of ground combustion machine combustion chamber Download PDFInfo
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- CN105423344B CN105423344B CN201610015950.0A CN201610015950A CN105423344B CN 105423344 B CN105423344 B CN 105423344B CN 201610015950 A CN201610015950 A CN 201610015950A CN 105423344 B CN105423344 B CN 105423344B
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- Prior art keywords
- inner liner
- combustion chamber
- tube structure
- burner inner
- flame tube
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/425—Combustion chambers comprising a tangential or helicoidal arrangement of the flame tubes
Abstract
A kind of flame tube structure of ground combustion machine combustion chamber provided by the present invention, its basic structure are spiral spring, include the ring segment of four sections of Diameter Gradual Changes, and this flame tube structure is simple, remove from and are separately provided Cooling Holes, the procedure of processing of blending hole.Structure of the invention by changing main chamber burner inner liner, change propagation of the sound wave in main chamber, and then oscillation of sound pressure is not remained constant with the phase difference that HRR fluctuates, so as to prevent the generation of thermal acoustic oscillation.Mixed gas uniformly enters from the gap of spring burner inner liner wall in the present invention, can make fuel and air mixes more uniformly, reduce the appearance of localized hyperthermia's degree gradient, improve the service life of combustion chamber, NOx discharge can also be significantly reduced.
Description
Technical field
The present invention relates to gas turbine field, in particular to a kind of flame tube structure of ground combustion machine combustion chamber.
Background technology
With the development of heavy duty gas turbine technology, modern heavy-duty gas turbine pursues ultra-low emission, while towards
The direction of high temperature rise is developed, and the lifting of Gas Turbine proposes requirements at the higher level to main chamber design.
Main chamber is for the chemical energy in combustion gas is changed into heat energy, and the pressure-air after compressor pressure is heated
Allow temperature before to turbine, to enter the device of turbine acting.Burner inner liner is the main building block of combustion chamber, and starts
One of most important heating part of machine, while burner inner liner is the part that failure is most in combustion chamber, and limitation engine life
Critical component.Due to the demand for development of modern burner inner liner cooling technology, the structure of burner inner liner becomes to become increasingly complex.Burner inner liner
It is perforate thin-wall construction, not only the physical dimension difference of cylinder is big, and the cooling gas of many different pore sizes is also provided with barrel
Fenestra, blending hole are entered with ensureing to account for the cooling tolerance of total tolerance 20% from burner inner liner side wall.Such open-celled structure not only adds
Work is complicated, causes stress concentration phenomenon easily occur there is very big thermograde in burner inner liner Temperature Distribution.
In order to reduce NOx emission and obtain higher efficiency of combustion, modern gas turbines combustion chamber uses more and more
The combustion system of Fuel-air premix.But premixed combustion is more also easy to produce oscillatory occurences --- sound wave, hydrodynamics and heat release it
Interphase interaction.When vibration occurs, it can decline systematic function along with thermal discharge and the fluctuation of pressure and reduce burning
The service life of room, therefore the design of combustion system must assure that can avoid or control oscillatory occurences.
The content of the invention
The technical problem to be solved in the present invention is to provide a kind of flame tube structure of ground combustion machine, reduction localized hyperthermia can be made
The appearance of gradient is spent, also greatly reduces NOx discharge, while prevent the generation of thermal acoustic oscillation.
The present invention solves above-mentioned technical problem by following technological means：Its basic structure is spiral spring, including four
The ring segment of section Diameter Gradual Change.
The segment length of burner inner liner four is equal, to be not 90mm~110mm.
The first paragraph front end of the burner inner liner and the 4th section of rear end are fixedly connected with combustion box.
The direction of rotation of the burner inner liner first paragraph spiral is revolved for left hand, and second segment revolves for the right hand, and the 3rd section is that left hand revolves,
4th section is that the right hand revolves.
As a further improvement on the present invention：The first paragraph of burner inner liner is straight barrel type, a diameter of flaring of second and third section
Type, expansion half-angle are 4~6 °, and the 4th section of a diameter of flaring type, expansion half-angle is 3~4 °.
As the preferred embodiment of the present invention：Gap (i.e. pitch and the difference of spring steel diameter) width of first paragraph spring
For 0.1mm~0.4mm, the gap width of second and third section of spring is 0.9~1.1mm, and the gap width of the 4th section of spring is 0.4
~0.8mm.
Following beneficial effect can be obtained using the present invention：
1) structure of the invention by changing main chamber burner inner liner, changes propagation of the sound wave in main chamber, enters
And oscillation of sound pressure and the phase difference that HRR fluctuates is not remained constant, while spring has compensator or trimmer pressure in itself
Effect, so as to effectively prevent the generation of thermal acoustic oscillation.
2) mixed gas uniformly enters from the gap of spring burner inner liner wall in the present invention, eliminates and is separately provided cooling
Hole, the procedure of processing of blending hole, and can make that fuel and air mix more uniformly, reduce going out for localized hyperthermia's degree gradient
It is existing, the service life of combustion chamber is improved, also greatly reduces NOx discharge.
Brief description of the drawings
Fig. 1：The section view equal axes axonometric drawing of the example of the present invention
Fig. 2：The longitudinal sectional view of the present invention
Embodiment
The present invention is described in further detail with reference to the accompanying drawings and examples：
A kind of flame tube structure of ground combustion machine combustion chamber of the present embodiment, the burner inner liner wall is by screw type spring
Steel is formed, including four sections be sequentially connected, and four segment length are equal, to be not 90mm~110mm.As shown in Fig. 2 burner inner liner
The direction of rotation of one section of 1 spiral is revolved for left hand, and gap (i.e. pitch and the difference of spring steel diameter) width of first paragraph spring is
0.1mm~0.4mm, and spring burner inner liner diameter is constant.As shown in figure 1, outside first paragraph burner inner liner initiating terminal and main cyclone cylinder
The port of export of wall 8 is connected, while is fixedly connected with combustion box 7 by cylindrical columns 6, and cylindrical columns 6 have four, in week
It is evenly distributed upwards.There is the cooling mixed gas for accounting for combustion chamber total air 20% in outside between main cyclone drum outer wall 8 and casing 7
Gap enters combustion chamber, and first paragraph burner inner liner diameter is constant, and air-flow only serves cooling effect to this section.
As shown in Fig. 2 a diameter of flaring type of second and third section of burner inner liner, expansion half-angle is 4~6 °, and second segment is the right hand
Rotation, the 3rd section is that left hand revolves, and the gap width of second and third section of spring is 0.9~1.1mm.As shown in figure 1, when cooling blending is empty
When flow of air is to second and third section, most of dilution air can be entered in burner inner liner by larger gap and the structure extended out
Portion participates in burning, and the gap of the burner inner liner of this part and expansion angle can effectively control the air capacity for participating in burning.
As shown in Fig. 2 the 4th section of 4 spirals of burner inner liner revolve for the right hand, oppositely oriented, the gap of spring with a upper spiral
Width is 0.4~0.8mm, a diameter of flaring type, expands half-angle and is reduced to 3~4 °, reduce the entrance of blending tolerance.The structure can
To change propagation of the sound wave in main chamber, and then the phase difference for making oscillation of sound pressure be fluctuated with HRR will not be protected all the time
Hold constant, while spring has the function that compensator or trimmer pressure in itself, so as to effectively prevent the generation of thermal acoustic oscillation.As shown in figure 1,
Burner inner liner is fixedly connected for the 4th section 4 by pillar 5 with casing 7, and the pillar 5 has 4, is evenly distributed in the circumferential.
Above-described embodiment is only a preferred embodiment of the present invention, should not turn into the limit to the scope of the present invention
System, the unlimited above-described embodiment of embodiment of the invention.
Claims (5)
1. a kind of flame tube structure of ground combustion machine combustion chamber, it is characterised in that the burner inner liner wall is by screw type spring
Steel is formed, and burner inner liner includes four sections be sequentially connected vertically, and four segment length are equal, respectively 90mm~110mm.
2. a kind of flame tube structure of ground combustion machine combustion chamber according to claim 1 is characterized in that, the burner inner liner
First paragraph for straight barrel type, the gap width of spring is 0.1mm~0.4mm, and the direction of rotation of spiral is left hand rotation, wherein
The gap of spring refers to the difference of pitch and spring steel diameter.
A kind of 3. flame tube structure of ground combustion machine combustion chamber according to claim 1 or 2, it is characterised in that the fire
A diameter of flaring type of second and third section of flame cylinder, expansion half-angle is 4~6 °, and the gap width of spring is 0.9~1.1mm,
The direction of rotation of the spiral of second and third section is respectively right hand rotation and left hand rotation.
4. the flame tube structure of a kind of ground combustion machine combustion chamber according to claim 1 or 2, it is characterised in that described
4th section of a diameter of flaring type of burner inner liner, expansion half-angle are 3~4 °, the gap width of spring for 0.4~
0.8mm, the direction of rotation of the 4th section of spiral are revolved for the right hand.
A kind of 5. flame tube structure of ground combustion machine combustion chamber according to claim 1, it is characterised in that the flame
The first paragraph front end and the 4th section of rear end of cylinder are fixedly connected with combustion box.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610015950.0A CN105423344B (en) | 2016-01-12 | 2016-01-12 | A kind of flame tube structure of ground combustion machine combustion chamber |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610015950.0A CN105423344B (en) | 2016-01-12 | 2016-01-12 | A kind of flame tube structure of ground combustion machine combustion chamber |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105423344A CN105423344A (en) | 2016-03-23 |
| CN105423344B true CN105423344B (en) | 2017-12-29 |
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| CN201610015950.0A Active CN105423344B (en) | 2016-01-12 | 2016-01-12 | A kind of flame tube structure of ground combustion machine combustion chamber |
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Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR3081925B1 (en) * | 2018-05-29 | 2020-08-14 | Safran Aircraft Engines | PROCESS FOR MONITORING THE SPARK PLUGS OF A TURBOMOTOR USING A VIBRATORY MEASUREMENT |
| CN109737450B (en) * | 2018-12-11 | 2019-12-03 | 北京航空航天大学 | Combustion chambers burn oscillation control device and combustion chambers burn oscillation control method |
| CN112050255B (en) * | 2020-09-18 | 2022-04-22 | 中国航发四川燃气涡轮研究院 | Flame tube adopting clearance rotational flow cooling |
| CN115325564B (en) * | 2022-07-21 | 2023-06-30 | 北京航空航天大学 | Method and device for suppressing combustion oscillation by combining pneumatic diversion |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB742657A (en) * | 1953-01-16 | 1955-12-30 | Rolls Royce | Improvements in or relating to hot-gas-conveying ducting |
| GB859805A (en) * | 1958-07-21 | 1961-01-25 | Gen Motors Corp | Improvements relating to gas turbine engine combustion systems |
| CN1487237A (en) * | 2002-08-22 | 2004-04-07 | 通用电气公司 | Combustor radome for gas combustion worm gear engine |
| CN201025371Y (en) * | 2007-02-09 | 2008-02-20 | 沈阳黎明航空发动机(集团)有限责任公司 | A flame canister with corset structure |
| CN202813443U (en) * | 2012-09-12 | 2013-03-20 | 中国科学院工程热物理研究所 | Lean pre-mixing combustion room of gas turbine |
| CN104406197A (en) * | 2014-11-24 | 2015-03-11 | 中国科学院工程热物理研究所 | Low-emission reverse flow combustor adopting radial swirl injection and fuel oil grading schemes |
| CN104896512A (en) * | 2015-05-11 | 2015-09-09 | 北京航空航天大学 | Low-emission natural gas combustion chamber with wide stable working range |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2007113888A (en) * | 2005-10-24 | 2007-05-10 | Kawasaki Heavy Ind Ltd | Combustor structure of gas turbine engine |
-
2016
- 2016-01-12 CN CN201610015950.0A patent/CN105423344B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB742657A (en) * | 1953-01-16 | 1955-12-30 | Rolls Royce | Improvements in or relating to hot-gas-conveying ducting |
| GB859805A (en) * | 1958-07-21 | 1961-01-25 | Gen Motors Corp | Improvements relating to gas turbine engine combustion systems |
| CN1487237A (en) * | 2002-08-22 | 2004-04-07 | 通用电气公司 | Combustor radome for gas combustion worm gear engine |
| CN201025371Y (en) * | 2007-02-09 | 2008-02-20 | 沈阳黎明航空发动机(集团)有限责任公司 | A flame canister with corset structure |
| CN202813443U (en) * | 2012-09-12 | 2013-03-20 | 中国科学院工程热物理研究所 | Lean pre-mixing combustion room of gas turbine |
| CN104406197A (en) * | 2014-11-24 | 2015-03-11 | 中国科学院工程热物理研究所 | Low-emission reverse flow combustor adopting radial swirl injection and fuel oil grading schemes |
| CN104896512A (en) * | 2015-05-11 | 2015-09-09 | 北京航空航天大学 | Low-emission natural gas combustion chamber with wide stable working range |
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| CN105423344A (en) | 2016-03-23 |
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| CB03 | Change of inventor or designer information |
Inventor after: Zhang Qun Inventor after: Kou Rui Inventor after: Song Yaheng Inventor after: Li Chengyu Inventor after: Xing Li Inventor after: Li Chaochao Inventor after: Wang Yuming Inventor after: Yang Shengzhe Inventor after: Li Yifei Inventor before: Zhang Qun Inventor before: Xing Li Inventor before: Li Chaochao Inventor before: Wang Yuming Inventor before: Yang Shengzhe |
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Effective date of registration: 20200407 Address after: Warner Jinghu garden 300300 Tianjin city Dongli District 2-103 room Patentee after: CHENGLI AVIATION TECHNOLOGY Co.,Ltd. Address before: Beilin District Shaanxi province Xi'an City friendship road 710072 No. 127 Patentee before: Northwestern Polytechnical University |
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Address after: Room 2-103, Warner Jinghu Garden, Dongli District, Tianjin Patentee after: Establishment of Aviation Co., Ltd Address before: Room 2-103, Warner Jinghu Garden, Dongli District, Tianjin Patentee before: CHENGLI AVIATION TECHNOLOGY Co.,Ltd. |
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