CN105716112A - Method used for regulating temperature field of combustion chamber - Google Patents
Method used for regulating temperature field of combustion chamber Download PDFInfo
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- CN105716112A CN105716112A CN201410741454.4A CN201410741454A CN105716112A CN 105716112 A CN105716112 A CN 105716112A CN 201410741454 A CN201410741454 A CN 201410741454A CN 105716112 A CN105716112 A CN 105716112A
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- air
- combustion chamber
- inner liner
- blending hole
- burner inner
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Abstract
The invention provides a method used for regulating the temperature field of a combustion chamber. Mixing holes with deflection angles in the radial direction are processed in the inner and outer walls of a flame tube of the combustion chamber, the diameter of the mixing holes is 8-30mm, and the number of the mixing holes is two to three times that of nozzles. The work environment of the mixing holes is as follows: air between an outer casing of the combustion chamber and the outer wall of the flame tube enters the flame tube through the mixing holes in the outer wall, and air between an inner casing of the combustion chamber and the inner wall of the flame tube enters the flame tube through the mixing holes in the inner wall. The method has the advantages that both fuel gas main flow and mixed air flow have certain circumferential component velocities, so that air can be conveniently mixed with fuel gas, and the peripheral temperature distribution unevenness of the main combustion chamber is reduced; as air flow has certain angle with the axial direction, air mixing distance is prolonged without changing the length of the flame tube, and the mixing effect is enhanced; and the weight of a gas turbine is reduced, and the efficiency of the gas turbine is improved.
Description
Technical field
The present invention relates to chamber temperature field control field, particularly to a kind of method regulating chamber temperature field.
Background technology
In order to obtain satisfied combustor exit temperature field, blending hole is generally adopted to be adjusted.Current blending hole is generally adopted the mode of radial air inlet, and combustor exit air flows vertically, and for the requirement of satisfied blending time, blending section is longer.It addition, turbine rotor wishes that airintake direction has certain angle, between combustor exit and turbine rotor, therefore it is provided with nozzle ring to regulate airflow direction.
Summary of the invention
It is an object of the invention to the turbine part for gas-turbine unit and provide the air-flow with prewhirl angle, shorten the length of combustor simultaneously, reduce the weight of electromotor, spy provides a kind of method regulating chamber temperature field.
The invention provides a kind of method regulating chamber temperature field, it is characterized in that: the method for described adjustment chamber temperature field, the blending hole at work and radial direction belt deflector angle on the inside and outside wall of combustion chamber flame drum, the diameter of blending hole is between Φ 8～Φ 30mm, and the quantity of blending hole is 2～3 times of nozzle quantity；
The working environment of blending hole is: the air between outer combustion case 6 and burner inner liner outer wall 2 enters burner inner liner by outer wall blending hole 1；In combustor, the air between casing 7 and burner inner liner inwall 3 enters burner inner liner by inwall blending hole 4.
The blending hole at described work on the inside and outside wall of combustion chamber flame drum and radial direction belt deflector angle, and the angle between radial direction is between 4 °～15 °.
Adjust the airflow direction in burner inner liner, it is possible to adjust Jet Penetration Depth by increasing the mode of sleeve or flange in blending hole；Due to air-flow and axially between have certain angle, the distance therefore blended in the situation downstream that burner inner liner length is constant is lengthened out, and can shorten further when ensureing to blend the length of burner inner liner apart from constant.
Simultaneously because the airflow direction of combustor exit has been able to meet the demand of turbine rotor, will no longer be required to turbine nozzle vane, so can make the length of electromotor and the contraction in length of engine shaft, the rigidity tool of loss of weight and raising axle is had certain effect.
Primary combustor chamber exit Uniformity of Temperature Field is the important parameter of examination Combustion chamber design quality, and conventional combustion room is provided, by blending hole, the purpose that high-temperature fuel gas is diluted reaching increasing export Uniformity of Temperature Field by cooling air-flow.The distribution of blending hole and the inhomogeneities of primary zone fuel distribution directly affect primary combustor chamber exit thermo parameters method.In addition combustor exit adopts turbine stator vane raised speed by air and make it be supplied to turbine rotor at an angle.Due to the existence of stator blade, portion of air is used for cooling down blade, decreases the quantity entering burner inner liner air, makes the temperature rise of combustor improve；Stators adds the length of engine shaft, the weight of electromotor simultaneously.The technical scheme that a kind of new burner inner liner air blends is proposed, while regulating Temperature Distribution, for solving the contradiction that between gas-turbine combustion chamber outlet and turbine rotor, air-flow angle is inconsistent.
Advantages of the present invention:
The method of adjustment chamber temperature field of the present invention, combustion gas main flow and blending air-flow all have certain circumferential component velocity, are so conducive to blending between the two, alleviate the even property of circumferential asymmetry of main chamber Temperature Distribution；Due to air-flow and axially between have certain angle, the distance therefore blended in the situation downstream that burner inner liner length is constant is lengthened out, and mixing effect is enhanced；If ensureing to blend apart from constant, the length of burner inner liner can shorten further.
The blending hole of deflection can make the flow direction of primary air change, to promote primary combustor chamber exit uniformity and to adapt to the turbine rotor requirement to airflow direction.So not only improve primary combustor chamber exit temperature homogeneity, extend the life-span of turbine part, and gas turbine can be no longer necessary to nozzle ring: the weight of gas turbine can be reduced on the one hand, can save the participation burning efficiency to improve gas turbine for the air of guider cooling on the other hand.
Accompanying drawing explanation
Below in conjunction with drawings and the embodiments, the present invention is further detailed explanation:
Fig. 1 is the blending schematic diagram regulating chamber temperature field.
Detailed description of the invention
Embodiment 1
Present embodiments provide a kind of method regulating chamber temperature field, it is characterized in that: the method for described adjustment chamber temperature field, the blending hole at work and radial direction belt deflector angle on the inside and outside wall of combustion chamber flame drum, the diameter of blending hole is Φ 8mm, and the quantity of blending hole is 2 times of nozzle quantity；
The working environment of blending hole is: the air between outer combustion case 6 and burner inner liner outer wall 2 enters burner inner liner by outer wall blending hole 1；In combustor, the air between casing 7 and burner inner liner inwall 3 enters burner inner liner by inwall blending hole 4.
The blending hole at described work on the inside and outside wall of combustion chamber flame drum and radial direction belt deflector angle, and the angle between radial direction is 4 °.
Adjust the airflow direction in burner inner liner, it is possible to adjust Jet Penetration Depth by increasing the mode of sleeve or flange in blending hole；Due to air-flow and axially between have certain angle, the distance therefore blended in the situation downstream that burner inner liner length is constant is lengthened out, and can shorten further when ensureing to blend the length of burner inner liner apart from constant.
Simultaneously because the airflow direction of combustor exit has been able to meet the demand of turbine rotor, will no longer be required to turbine nozzle vane, so can make the length of electromotor and the contraction in length of engine shaft, the rigidity tool of loss of weight and raising axle is had certain effect.
Primary combustor chamber exit Uniformity of Temperature Field is the important parameter of examination Combustion chamber design quality, and conventional combustion room is provided, by blending hole, the purpose that high-temperature fuel gas is diluted reaching increasing export Uniformity of Temperature Field by cooling air-flow.The distribution of blending hole and the inhomogeneities of primary zone fuel distribution directly affect primary combustor chamber exit thermo parameters method.In addition combustor exit adopts turbine stator vane raised speed by air and make it be supplied to turbine rotor at an angle.Due to the existence of stator blade, portion of air is used for cooling down blade, decreases the quantity entering burner inner liner air, makes the temperature rise of combustor improve；Stators adds the length of engine shaft, the weight of electromotor simultaneously.The technical scheme that a kind of new burner inner liner air blends is proposed, while regulating Temperature Distribution, for solving the contradiction that between gas-turbine combustion chamber outlet and turbine rotor, air-flow angle is inconsistent.
Embodiment 2
Present embodiments provide a kind of method regulating chamber temperature field, it is characterized in that: the method for described adjustment chamber temperature field, the blending hole at work and radial direction belt deflector angle on the inside and outside wall of combustion chamber flame drum, the diameter of blending hole is Φ 20mm, and the quantity of blending hole is 3 times of nozzle quantity；
The working environment of blending hole is: the air between outer combustion case 6 and burner inner liner outer wall 2 enters burner inner liner by outer wall blending hole 1；In combustor, the air between casing 7 and burner inner liner inwall 3 enters burner inner liner by inwall blending hole 4.
The blending hole at described work on the inside and outside wall of combustion chamber flame drum and radial direction belt deflector angle, and the angle between radial direction is 10 °.
Adjust the airflow direction in burner inner liner, it is possible to adjust Jet Penetration Depth by increasing the mode of sleeve or flange in blending hole；Due to air-flow and axially between have certain angle, the distance therefore blended in the situation downstream that burner inner liner length is constant is lengthened out, and can shorten further when ensureing to blend the length of burner inner liner apart from constant.
Simultaneously because the airflow direction of combustor exit has been able to meet the demand of turbine rotor, will no longer be required to turbine nozzle vane, so can make the length of electromotor and the contraction in length of engine shaft, the rigidity tool of loss of weight and raising axle is had certain effect.
Primary combustor chamber exit Uniformity of Temperature Field is the important parameter of examination Combustion chamber design quality, and conventional combustion room is provided, by blending hole, the purpose that high-temperature fuel gas is diluted reaching increasing export Uniformity of Temperature Field by cooling air-flow.The distribution of blending hole and the inhomogeneities of primary zone fuel distribution directly affect primary combustor chamber exit thermo parameters method.In addition combustor exit adopts turbine stator vane raised speed by air and make it be supplied to turbine rotor at an angle.Due to the existence of stator blade, portion of air is used for cooling down blade, decreases the quantity entering burner inner liner air, makes the temperature rise of combustor improve；Stators adds the length of engine shaft, the weight of electromotor simultaneously.The technical scheme that a kind of new burner inner liner air blends is proposed, while regulating Temperature Distribution, for solving the contradiction that between gas-turbine combustion chamber outlet and turbine rotor, air-flow angle is inconsistent.
Embodiment 3
Present embodiments provide a kind of method regulating chamber temperature field, it is characterized in that: the method for described adjustment chamber temperature field, the blending hole at work and radial direction belt deflector angle on the inside and outside wall of combustion chamber flame drum, the diameter of blending hole is Φ 30mm, and the quantity of blending hole is 3 times of nozzle quantity；
The working environment of blending hole is: the air between outer combustion case 6 and burner inner liner outer wall 2 enters burner inner liner by outer wall blending hole 1；In combustor, the air between casing 7 and burner inner liner inwall 3 enters burner inner liner by inwall blending hole 4.
The blending hole at described work on the inside and outside wall of combustion chamber flame drum and radial direction belt deflector angle, and the angle between radial direction is 15 °.
Adjust the airflow direction in burner inner liner, it is possible to adjust Jet Penetration Depth by increasing the mode of sleeve or flange in blending hole；Due to air-flow and axially between have certain angle, the distance therefore blended in the situation downstream that burner inner liner length is constant is lengthened out, and can shorten further when ensureing to blend the length of burner inner liner apart from constant.
Simultaneously because the airflow direction of combustor exit has been able to meet the demand of turbine rotor, will no longer be required to turbine nozzle vane, so can make the length of electromotor and the contraction in length of engine shaft, the rigidity tool of loss of weight and raising axle is had certain effect.
Primary combustor chamber exit Uniformity of Temperature Field is the important parameter of examination Combustion chamber design quality, and conventional combustion room is provided, by blending hole, the purpose that high-temperature fuel gas is diluted reaching increasing export Uniformity of Temperature Field by cooling air-flow.The distribution of blending hole and the inhomogeneities of primary zone fuel distribution directly affect primary combustor chamber exit thermo parameters method.In addition combustor exit adopts turbine stator vane raised speed by air and make it be supplied to turbine rotor at an angle.Due to the existence of stator blade, portion of air is used for cooling down blade, decreases the quantity entering burner inner liner air, makes the temperature rise of combustor improve；Stators adds the length of engine shaft, the weight of electromotor simultaneously.The technical scheme that a kind of new burner inner liner air blends is proposed, while regulating Temperature Distribution, for solving the contradiction that between gas-turbine combustion chamber outlet and turbine rotor, air-flow angle is inconsistent.
Claims (2)
1. the method regulating chamber temperature field, it is characterized in that: the method for described adjustment chamber temperature field, the blending hole at work and radial direction belt deflector angle on the inside and outside wall of combustion chamber flame drum, the diameter of blending hole is between Φ 8～Φ 30mm, and the quantity of blending hole is 2～3 times of nozzle quantity；
The working environment of blending hole is: the air between outer combustion case (6) and burner inner liner outer wall (2) enters burner inner liner by outer wall blending hole (1)；In combustor, the air between casing (7) and burner inner liner inwall (3) enters burner inner liner by inwall blending hole (4).
2. the method for the adjustment chamber temperature field described in claim 1, it is characterised in that: the blending hole at described work on the inside and outside wall of combustion chamber flame drum and radial direction belt deflector angle, and the angle between radial direction is between 4 °～15 °.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410741454.4A CN105716112A (en) | 2014-12-04 | 2014-12-04 | Method used for regulating temperature field of combustion chamber |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410741454.4A CN105716112A (en) | 2014-12-04 | 2014-12-04 | Method used for regulating temperature field of combustion chamber |
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| CN105716112A true CN105716112A (en) | 2016-06-29 |
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| CN201410741454.4A Pending CN105716112A (en) | 2014-12-04 | 2014-12-04 | Method used for regulating temperature field of combustion chamber |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107576502A (en) * | 2017-08-10 | 2018-01-12 | 中国北方发动机研究所(天津) | A kind of turbocharger test platform combustion chamber with mixing section |
| CN112717739A (en) * | 2020-12-04 | 2021-04-30 | 中国科学技术大学 | Chemical substance mixing device and method suitable for high-speed flow field environment |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB899213A (en) * | 1959-12-24 | 1962-06-20 | Havilland Engine Co Ltd | Combustion chambers |
| CN1160150A (en) * | 1995-06-02 | 1997-09-24 | 亚瑞亚·勃朗勃威力有限公司 | Burning chamber |
| CN102175044A (en) * | 2011-03-04 | 2011-09-07 | 北京航空航天大学 | Mixing combustion guide coupling structure of combustion chamber |
| CN202419700U (en) * | 2011-12-28 | 2012-09-05 | 中航商用航空发动机有限责任公司 | Multi-inclined-hole flame tube wall plate, flame tube and gas turbine combustion chamber |
| CN203464332U (en) * | 2013-09-04 | 2014-03-05 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Transition section of combustion chamber of combustion gas turbine |
-
2014
- 2014-12-04 CN CN201410741454.4A patent/CN105716112A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB899213A (en) * | 1959-12-24 | 1962-06-20 | Havilland Engine Co Ltd | Combustion chambers |
| CN1160150A (en) * | 1995-06-02 | 1997-09-24 | 亚瑞亚·勃朗勃威力有限公司 | Burning chamber |
| CN102175044A (en) * | 2011-03-04 | 2011-09-07 | 北京航空航天大学 | Mixing combustion guide coupling structure of combustion chamber |
| CN202419700U (en) * | 2011-12-28 | 2012-09-05 | 中航商用航空发动机有限责任公司 | Multi-inclined-hole flame tube wall plate, flame tube and gas turbine combustion chamber |
| CN203464332U (en) * | 2013-09-04 | 2014-03-05 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Transition section of combustion chamber of combustion gas turbine |
Non-Patent Citations (1)
| Title |
|---|
| 祁海鹰: "燃烧室出口温度分布偏差的机理", 《燃烧科学与技术》 * |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107576502A (en) * | 2017-08-10 | 2018-01-12 | 中国北方发动机研究所(天津) | A kind of turbocharger test platform combustion chamber with mixing section |
| CN107576502B (en) * | 2017-08-10 | 2019-11-12 | 中国北方发动机研究所(天津) | A kind of turbocharger test platform combustion chamber with mixing section |
| CN112717739A (en) * | 2020-12-04 | 2021-04-30 | 中国科学技术大学 | Chemical substance mixing device and method suitable for high-speed flow field environment |
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Application publication date: 20160629 |