CN113702058A - Combustion test method for pressure reduction simulation of combustion chamber of gas turbine - Google Patents
Combustion test method for pressure reduction simulation of combustion chamber of gas turbine Download PDFInfo
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- CN113702058A CN113702058A CN202111087279.8A CN202111087279A CN113702058A CN 113702058 A CN113702058 A CN 113702058A CN 202111087279 A CN202111087279 A CN 202111087279A CN 113702058 A CN113702058 A CN 113702058A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
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Abstract
The invention discloses a combustion test method for pressure reduction simulation of a gas turbine combustion chamber, which comprises the following steps: controlling the inlet air flow of the test combustion chamber and the total pressure of the inlet air of the test combustion chamber according to a simulation criterion H, and performing a simulation test in the test combustion chamber; simulation criterion H G/Pn＝G0/P0 n. The combustion test method provided by the invention is low in test cost and high in test result accuracy.
Description
Technical Field
The invention relates to the technical field of gas turbine combustor tests, in particular to a combustion test method for depressurization simulation of a gas turbine combustor.
Background
The development process of gas turbine combustors has a strong dependence on combustor tests, and many tests can be performed under a simulation of relatively low combustor inlet air pressure in order to reduce the test cost of the gas turbine combustors. Because the working process of the gas turbine combustor is very complicated, the design method of the gas turbine combustor still adopts an experience-semi-experience method. Accurate and real combustion efficiency cannot be obtained.
Disclosure of Invention
In view of the above-mentioned drawbacks and deficiencies of the prior art, it is desirable to provide a combustion test method for a gas turbine combustor depressurization simulation with low test cost and high test result accuracy.
The invention provides a combustion test method for depressurization simulation of a gas turbine combustor, which comprises the following steps:
controlling the inlet air flow of the test combustion chamber and the total pressure of the inlet air of the test combustion chamber according to a simulation criterion H, and performing a simulation test in the test combustion chamber;
simulation standardThen H is G/Pn＝G0/P0 n；
When P is less than or equal to 3.5, n is 1.5;
when 5 is more than P and more than 3.5, n is 1.3;
when P is more than or equal to 5, n is 1.0;
wherein: g is the inlet air flow of the test combustion chamber, and the unit is Kg/s;
p is total pressure of inlet air of the test combustion chamber, and the unit is Kg/cm2；
n is a pressure index;
G0the unit is Kg/s of the real combustion chamber inlet air flow;
P0the total pressure of air at the inlet of a real combustion chamber is Kg/cm2。
Furthermore, the geometric dimension of the inner ring cavity of the test combustion chamber and the arrangement of the flow channel are the same as those of the real combustion chamber.
Further, the oil-gas ratio of the test combustion chamber is the same as that of the real combustion chamber;
simulating an inlet air flow field of the test combustion chamber according to an outlet radial velocity profile of a compressor at the inlet of the real combustion chamber;
the outward air entraining amount of the test combustion chamber is the same as the outward air entraining amount of the real combustion chamber;
the air entraining proportion of the inner and outer annular cavities of the test combustion chamber is the same as that of the inner and outer annular cavities of the real combustion chamber;
the air entraining position of the test combustion chamber is the same as that of the real combustion chamber;
the inlet air temperature of the test combustor is the same as the inlet air temperature of the real combustor.
Compared with the prior art, the invention has the beneficial effects that:
the combustion test method of the invention is based on the simulation criterion H ═ G/Pn＝G0/P0 nCarrying out a pressure reduction simulation combustion test, and obtaining the inlet air flow G of the test combustion chamber matched with the total pressure P of the inlet air of the test combustion chamber under the condition of reducing the total pressure P of the inlet air of the test combustion chamber, so thatThe test chamber and the real chamber have the same simulation criteria H. The accuracy of the combustion chamber decompression simulation combustion test result is ensured. Under the condition that the total pressure P of the inlet air of the test combustion chamber is reduced, the requirement on the performance of test equipment is reduced, and the test cost is greatly saved.
It should be understood that the statements herein reciting aspects are not intended to limit the critical or essential features of any embodiment of the invention, nor are they intended to limit the scope of the invention. Other features of the present invention will become apparent from the following description.
Detailed Description
The following examples further illustrate the invention in detail. It is to be understood that the specific embodiments described herein are merely illustrative of the relevant invention and not restrictive of the invention. It should be noted that the embodiments and features of the embodiments may be combined with each other without conflict. The present invention will be described in detail below with reference to examples.
The embodiment of the invention provides a combustion test method for depressurization simulation of a combustion chamber of a gas turbine, which comprises the following steps:
controlling the inlet air flow of the test combustion chamber and the total pressure of the inlet air of the test combustion chamber according to a simulation criterion H, and performing a simulation test in the test combustion chamber;
simulation criterion H G/Pn＝G0/P0 n；
When P is less than or equal to 3.5, n is 1.5;
when 5 is more than P and more than 3.5, n is 1.3;
when P is more than or equal to 5, n is 1.0;
wherein: g is the inlet air flow of the test combustion chamber, and the unit is Kg/s;
p is total pressure of inlet air of the test combustion chamber, and the unit is Kg/cm2；
n is a pressure index;
G0the unit is Kg/s of the real combustion chamber inlet air flow;
P0the total pressure of air at the inlet of a real combustion chamber is Kg/cm2。
In the embodiment, a simulation criterion H of a pressure reduction simulation combustion test of a gas turbine combustor is provided, and the application condition of the pressure index n influencing the combustion efficiency is determined when the total pressure P of inlet air of the test combustor is under the low-pressure condition (P is less than or equal to 3.5, 5 is more than P is more than 3.5, and P is more than or equal to 5). Simulation criterion H G/Pn＝G0/P0 n，G0And P0The actual combustor inlet air flow and total inlet air pressure are known standard values, and the matching G is obtained by the P, n value defined by the invention. So that the test chamber has the same simulation criteria H as the real chamber.
The method provides a set of simulation criteria for the combustion efficiency test, clearly limits the pressure index n influencing the combustion efficiency of the combustion chamber, eliminates the blindness of the test, and ensures that the pressure reduction simulation combustion test result of the combustion chamber is consistent with the real combustion chamber, and is real and accurate.
Meanwhile, under the condition that the total pressure P of the inlet air of the test combustion chamber is reduced, the requirement on the performance of test equipment is reduced, and the test cost is greatly saved.
In the embodiment, the inner ring cavity geometry and the flow passage arrangement of the test combustion chamber are the same as those of the real combustion chamber. The test combustion chamber is arranged on the test platform, the internal structure of the test combustion chamber is completely the same as that of the real combustion chamber, and the authenticity of a test result is ensured.
For a single tube/annular tube combustor, a single flame tube fan test combustor may be employed. For the annular combustor, a single-head fan-shaped test combustor is not preferable due to the influence of the side wall, at least 3 flame tube heads are included in the fan-shaped test combustor, and test data of the flame tube heads close to two sides of the fan-shaped test combustor cannot be used.
In an embodiment, the fuel-air ratio of the test combustion chamber is the same as the fuel-air ratio of the real combustion chamber;
simulating an inlet air flow field of the test combustion chamber according to an outlet radial velocity profile of a gas compressor at the inlet of the real combustion chamber;
the outward air entraining amount of the test combustion chamber is the same as the outward air entraining amount of the real combustion chamber;
the air entraining proportion of the inner and outer annular cavities of the test combustion chamber is the same as that of the real combustion chamber;
the air entraining position of the test combustion chamber is the same as that of the real combustion chamber;
the inlet air temperature of the test chamber was the same as the inlet air temperature of the actual chamber.
In this embodiment, since the actual combustion chamber operates at a radially different speed of air sent from the compressor at the inlet thereof, in order to ensure the authenticity of the test result of the test combustion chamber, the inlet of the test combustion chamber is simulated by an air flow control device to achieve the same combustion environment as the actual combustion chamber.
Similarly, other test parameters of the test combustion chamber are consistent with those of the real combustion chamber, and therefore guarantee is provided for authenticity of test results.
In the description of the present specification, the description of the terms "embodiment" and the like means that a specific feature described in connection with the embodiment is included in an example of the present application. The above description is only a preferred embodiment of the present application and is not intended to limit the present application, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, improvement and the like made within the spirit and principle of the present application shall be included in the protection scope of the present application.
Claims (3)
1. A combustion test method for depressurization simulation of a combustion chamber of a gas turbine is characterized by comprising the following steps of:
controlling the inlet air flow of the test combustion chamber and the total pressure of the inlet air of the test combustion chamber according to a simulation criterion H, and performing a simulation test in the test combustion chamber;
simulation criterion H G/Pn＝G0/P0 n；
When P is less than or equal to 3.5, n is 1.5;
when 5 is more than P and more than 3.5, n is 1.3;
when P is more than or equal to 5, n is 1.0;
wherein: g is the inlet air flow of the test combustion chamber, and the unit is Kg/s;
p is total pressure of inlet air of the test combustion chamber, and the unit is Kg/cm2；
n is a pressure index;
G0the unit is Kg/s of the real combustion chamber inlet air flow;
P0the total pressure of air at the inlet of a real combustion chamber is Kg/cm2。
2. The combustion testing method of claim 1, wherein the inner ring cavity geometry and flow channel arrangement of the test combustor are the same as the actual combustor.
3. The combustion testing method of claim 2, wherein the fuel-air ratio of the test combustion chamber is the same as the fuel-air ratio of the real combustion chamber;
simulating an inlet air flow field of the test combustion chamber according to an outlet radial velocity profile of a compressor at the inlet of the real combustion chamber;
the outward air entraining amount of the test combustion chamber is the same as the outward air entraining amount of the real combustion chamber;
the air entraining proportion of the inner and outer annular cavities of the test combustion chamber is the same as that of the inner and outer annular cavities of the real combustion chamber;
the air entraining position of the test combustion chamber is the same as that of the real combustion chamber;
the inlet air temperature of the test combustor is the same as the inlet air temperature of the real combustor.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202111087279.8A CN113702058A (en) | 2021-09-16 | 2021-09-16 | Combustion test method for pressure reduction simulation of combustion chamber of gas turbine |
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| CN202111087279.8A CN113702058A (en) | 2021-09-16 | 2021-09-16 | Combustion test method for pressure reduction simulation of combustion chamber of gas turbine |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2003172198A (en) * | 2001-12-06 | 2003-06-20 | Osaka Gas Co Ltd | Combustion state simulation method |
| CN104750066A (en) * | 2015-02-10 | 2015-07-01 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Combustion process control and optimization system for combustion gas turbine |
| CN108286484A (en) * | 2017-12-29 | 2018-07-17 | 上海交通大学 | Realize the spraying forming method of diesel combustion similitude |
| KR102178641B1 (en) * | 2019-07-19 | 2020-11-13 | 국방과학연구소 | Pneumatic test apparatus for propulsion simulation having variable simulated combustor volume and pneumatic test system comprising the same |
| CN112550758A (en) * | 2020-12-03 | 2021-03-26 | 中国航发沈阳发动机研究所 | Method for obtaining actual performance of each part of engine under complete machine condition |
-
2021
- 2021-09-16 CN CN202111087279.8A patent/CN113702058A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2003172198A (en) * | 2001-12-06 | 2003-06-20 | Osaka Gas Co Ltd | Combustion state simulation method |
| CN104750066A (en) * | 2015-02-10 | 2015-07-01 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Combustion process control and optimization system for combustion gas turbine |
| CN108286484A (en) * | 2017-12-29 | 2018-07-17 | 上海交通大学 | Realize the spraying forming method of diesel combustion similitude |
| KR102178641B1 (en) * | 2019-07-19 | 2020-11-13 | 국방과학연구소 | Pneumatic test apparatus for propulsion simulation having variable simulated combustor volume and pneumatic test system comprising the same |
| CN112550758A (en) * | 2020-12-03 | 2021-03-26 | 中国航发沈阳发动机研究所 | Method for obtaining actual performance of each part of engine under complete machine condition |
Non-Patent Citations (2)
| Title |
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| 朱杰文等: "燃气轮机燃烧室模化试验方法研究", 《上海电力学院学报》, vol. 35, no. 2 * |
| 郭明焕等: "N准则及其特点", 《中国航空学会第十一届燃烧与传热传质学术会议论文集》, pages 101 - 108 * |
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