Combustion chamber test flow testing method and system, electronic equipment and storage medium

Abstract

The invention discloses a combustion chamber test flow testing method and system, electronic equipment and a storage medium, and relates to the technical field of gas turbine combustion system flow testing. The method specifically comprises the steps of obtaining a combustion chamber test piece reference effective area through flow characteristic independent measurement; carrying out system measurement twice on the test section, wherein the total effective area containing all leaks is obtained for the first time, and the effective area of the remaining part is obtained after air cavity leakage is eliminated for the second time; calculating the leakage area of the air cavity and the leakage area of the rear seal of the transition section based on the difference value; and finally, calculating the total air inlet flow of the test section according to a complete machine equivalence principle and formulating test working conditions. According to the method, the core technical problems that the system-level flow distribution characteristics are difficult to accurately obtain due to system complexity and sealing leakage in the full-size test of the heavy-duty gas turbine, and the equivalence of the head combustion condition and the whole machine cannot be ensured are solved, and a quantitative basis is provided for formulating a real and effective test working condition.

Description

Technical Field

[0001] This application relates to the field of flow testing technology for gas turbine combustion systems, and in particular to combustion chamber test flow testing methods, systems, electronic equipment, and storage media. Background Technology

[0002] As core equipment in power generation and propulsion, the performance and reliability of heavy-duty gas turbines are of paramount importance. The combustor, a key component of the gas turbine, relies on full-scale testing for independent design and development. Full-scale combustor testing aims to realistically simulate the overall operating environment of the turbine, assessing ignition performance, flameout boundary, combustion stability, and structural reliability. It is an indispensable and crucial step in demonstrating the feasibility of the design and guiding subsequent optimization and manufacturing.

[0003] To achieve effective simulation of the overall engine environment, the test system must accurately reproduce the aerodynamic state at the combustion chamber inlet. One of the core requirements is to ensure that the airflow participating in combustion at the combustion chamber head is strictly consistent with the overall engine design conditions. However, the structure of a full-scale test bench differs fundamentally from that of a real engine. The test section typically includes complex components such as air chambers and exhaust sections designed to simulate aerodynamic and structural conditions. The connections and seals between these components inevitably result in propellant leakage. Therefore, the total airflow entering the test system cannot be fully proportional to the design flow rate into the combustion chamber for reaction. Furthermore, the accuracy of the internal flow distribution of the manufactured combustion chamber test piece itself, ensuring it meets design expectations, also needs to be verified through testing.

[0004] Existing patent CN109632325A discloses a test method for flow distribution in the main combustion chamber of an aero-engine, which establishes a flow characteristic curve by blocking specific channels and measuring the pressure difference. However, this method is designed for relatively simple aero-engine combustion chambers, and its operating condition settings are not sensitive to leakage in the test system, mainly serving the manufacturing conformity verification of the test component itself.

[0005] Existing patent CN116222684A discloses a rectifier plate and testing system for a combustion chamber flow testing system. By setting up a rectifier structure to stabilize the airflow, it enables accurate measurement of the flow rate and pressure loss of key components in a single-tube combustion chamber. This approach focuses on the flow optimization and measurement of key components, and its system configuration and testing objectives differ significantly from the system-level flow distribution characteristics that need to be verified in full-scale tests of heavy-duty gas turbines.

[0006] In summary, existing patented technologies mainly focus on the specific testing needs of aero-engines or combustion chamber components. They have not yet provided effective system-level flow testing methods with good engineering reference value for the special and complex characteristics of full-scale testing of heavy-duty gas turbine combustion chambers, such as complex system structure, significant impact of sealing leakage, and the need to simultaneously verify the overall flow distribution characteristics of the test specimen and the test system. Summary of the Invention

[0007] Based on the current state of technology, in order to solve the problem that the system-level flow distribution characteristics are difficult to accurately obtain due to the complexity of the test system structure and sealing leakage in the full-scale test of the heavy-duty gas turbine combustor, this invention proposes a combustor test flow measurement method, system, electronic equipment and storage medium. It aims to provide key flow distribution design ideas and data support for the full-scale test in the research and development process of heavy-duty gas turbine combustors, and ensure the accuracy of the test conditions and the validity of the test results.

[0008] To achieve the above objectives, the first aspect of this application proposes a method for testing the flow rate of a combustion chamber, the specific technical solution of which is as follows: A method for testing the flow rate in a combustion chamber, the method comprising the following steps: S1. Independently measure the flow characteristics of the cooling structure on the transition section of the combustion chamber test piece to obtain its reference effective area; S2. On the assembled test section, perform the first system measurement to obtain the first total effective area including all leakage paths; S3. On the test section, after eliminating the influence of air cavity leakage through pressure control, a second system measurement is performed to obtain the second total effective area; S4. Based on the reference effective area, the first total effective area and the second total effective area, calculate the air cavity leakage area and the transition section post-seal leakage area; S5. Calculate the total intake flow rate of the test section based on the air cavity leakage area, the transition section rear seal leakage area, the reference effective area, and the overall machine design parameters, and formulate test conditions accordingly.

[0009] Furthermore, in step S1, a blocking and isolation measurement method is adopted. By blocking part of the cooling structure while maintaining the flow of the remaining cooling structure, the effective area of ​​each part of the cooling structure is measured in stages.

[0010] Furthermore, in step S1, the reference effective area includes the effective area of ​​the transition section cooling hole and the effective area of ​​the rear mounting edge cooling hole.

[0011] Further, in step S1, the reference effective area is calculated using the following formula. Where CdA is the effective area of ​​the unblocked cooling hole. ρ is the air mass flow rate, ρ is the inlet air density, and ∆p is the pressure difference between the pressure measuring point at the inlet of the flow test fixture and the atmospheric pressure at the outlet.

[0012] Further, in step S2, the first system measurement includes: sealing the head flow channel and transition section inlet of the combustion chamber test piece, introducing air at different pressures into the test section inlet, and measuring the total mass flow rate to obtain the first total effective area.

[0013] Further, in step S2, the first total effective area is the sum of the effective area of ​​air cavity leakage, the effective area of ​​transition section cooling hole, the effective area of ​​rear mounting edge cooling hole, and the effective area of ​​transition section rear seal.

[0014] Furthermore, in step S2, the head flow channel of the combustion chamber test piece is blocked with an end face blocking plate, and the inlet of the transition section is blocked with an elastic ball.

[0015] Further, in step S3, the second system measurement includes: maintaining the blocked state of the first system measurement, using closed-loop control to keep the pressure in the combustion cylinder consistent with the pressure in the air chamber to eliminate the pressure difference between them; introducing air at different pressures into the test section inlet and measuring the total mass flow rate to obtain the second total effective area.

[0016] Further, in step S3, the second total effective area is the sum of the effective area of ​​the cooling holes in the transition section, the effective area of ​​the cooling holes on the rear mounting edge, and the effective area of ​​the rear seal of the transition section.

[0017] Further, step S4 includes: The air cavity leakage area is calculated based on the first total effective area measured in step S2 and the second total effective area measured in step S3, using the following formula: in, The first total effective area, This is the second total effective area; Based on the above calculation results and the reference effective area measured in step S1 and the second total effective area measured in step S2, the leakage area of ​​the seal after the transition section is calculated. The calculation formula is as follows: in, This is the second total effective area. The area of ​​the cooling holes in the transition section. This refers to the area of ​​the cooling holes on the rear-mounted side.

[0018] Further, in step S5, the formula for calculating the total intake flow rate of the test section is: in, This represents the total mass flow rate of air introduced into the test section at the inlet. This refers to the total mass flow rate of air entering the combustion chamber at the design operating point in the overall machine environment. It is the sum of the flow area at the head of the combustion chamber test piece, the area of ​​the cooling holes in the transition section, and the area of ​​the cooling holes at the rear mounting edge; This refers to the effective leakage area of ​​the combustion chamber rear seal in the overall design of a gas turbine.

[0019] To achieve the above objectives, the second aspect of this application proposes a combustion chamber test flow rate testing system, the specific technical solution of which is as follows: A combustion chamber test flow rate testing system is provided for implementing the above-mentioned combustion chamber test flow rate testing method. The system includes: The flow testing fixture module is used for offline flow calibration of combustion chamber test specimens; A full-size test section module is used to simulate the overall machine environment and install the combustion chamber test piece; The sensor module, deployed on the flow testing fixture module and the full-size test section module, is used to measure pressure, temperature and mass flow rate; The pressure control module is used to control the pressure difference between the combustion cylinder and the air chamber in the full-size test section module; A data acquisition and control module, connected to the sensor module and the pressure control module, is used to acquire data and send control commands. The data processing and calculation module, connected to the data acquisition and control module, is used to execute the calculation logic of the method and output the final result.

[0020] By applying the above-described technical solution of the present invention, at least the following technical effects are achieved: 1. This invention systematically proposes and solves the problem of flow distribution under the coupling effect of "test system" and "test piece" in full-scale testing of heavy-duty gas turbines. It can not only verify the processing conformity of the test piece body, but also accurately quantify system-level leaks such as "air cavity leakage" and "transition section post-seal leakage" caused by installation and assembly, filling the gap in the existing technology in this field.

[0021] 2. This invention proposes a complete technical chain of "independent measurement - system measurement - difference calculation - operating condition formulation" to ensure the accuracy of test conditions and the validity of results. It accurately quantifies installation leaks that cannot be directly measured and calculates the total flow rate of the test section that can truly reproduce the head environment through the "equivalent conversion formula between the whole machine and the test bench," fundamentally ensuring that the test results can effectively characterize the overall machine's operating status.

[0022] 3. This invention does not depend on a specific model of test section or test piece structure. The "step-by-step isolation measurement" principle for complex cooling and sealing structures, the leakage elimination method based on differential pressure control, and the logic of system-level flow distribution characteristics described herein can be universally applied to full-scale tests of combustion chambers of heavy-duty gas turbines with various similar structures, establishing a clear, reliable, and reusable technical template for the test process in this field.

[0023] 4. This invention combines high-precision sensor measurement, closed-loop control, and highly operable manual blocking, ensuring the accuracy of key data measurement while avoiding extremely complex and expensive permanent modifications to the test section, significantly reducing test complexity and cost, and has outstanding engineering application value.

[0024] Additional aspects and advantages of this application will be set forth in part in the description which follows, and in part will be obvious from the description, or may be learned by practice of this application. Attached Figure Description

[0025] The accompanying drawings, which form part of this specification, are used to provide a further understanding of the invention. The illustrative embodiments of the invention and their descriptions are used to explain the invention and do not constitute an undue limitation of the invention. In the drawings: Figure 1 A schematic diagram of the full-size test section of the heavy-duty gas turbine combustion chamber in an embodiment of the present invention is shown; Figure 2 A schematic flowchart of a combustion chamber test flow rate testing method proposed in this invention is shown; Figure 3 A schematic diagram of the installation of the transition section and flow testing fixture of the combustion chamber test piece in an embodiment of the present invention is shown; Figure 4 A schematic diagram of the head sealing structure of the full-size test specimen of the combustion chamber in an embodiment of the present invention is shown; Figure 5 A schematic diagram of the framework of a combustion chamber test flow rate testing system proposed in this invention is shown; Figure 6 A computer program proposed in this invention is presented; Figure 7 An electronic device proposed in this invention is presented.

[0026] Reference numerals: 1-Intake diffuser; 2-Combustion cylinder; 3-Air chamber; 4-Combustion chamber head; 5-Guide bushing; 6-Transition section; 7-Rear mounting edge; 8-Sealing structure; 9-Transition section cooling hole; 10-Rear mounting edge cooling hole; 11-Process measurement fixture; 12-Transition section plug; 13-Arrangement of pressure and flow measurement points; 14-End face plug; 15-Elastic ball. Detailed Implementation

[0027] It should be noted that, unless otherwise specified, the embodiments and features described in the present invention can be combined with each other. The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0028] The present invention will be further described in detail below with reference to specific embodiments, which should not be construed as limiting the scope of protection claimed by the present invention.

[0029] See Figure 1 The diagram shows a structural schematic of a full-scale test of a heavy-duty gas turbine combustor according to the present invention. It mainly consists of two parts: a test section and a combustor test piece. The test section, serving as a fixed test platform, includes an intake diffuser 1 constructed to simulate the flow channel profile of the entire engine, an air cavity 3 located downstream of the intake diffuser 1 and simulating the shape of a combustion cylinder, a combustion cylinder 2 surrounding the air cavity, and a sealing structure 8 located at the interface between the test section and the combustor test piece. The test section provides the combustor test piece with intake and installation conditions similar to the overall engine environment. The combustor test piece, as the object to be tested, is housed within the air cavity 3 and includes a combustor head 4 (serving as the combustion reaction zone), a transition section 6, a flow guide bushing 5 fitted outside the transition section 6, and a rear mounting edge 7. Cooling holes 9 for the transition section and 10 for the rear mounting edge are respectively provided on the transition section 6 and the rear mounting edge 7.

[0030] Based on the above structure, the total intake air volume from the test section does not completely enter the combustion chamber head 4 to participate in combustion. Instead, there is a complex distribution and leakage path: part of the air flows through the cooling holes 9 of the transition section of the combustion chamber test piece and the cooling holes 10 of the rear mounting side to achieve the necessary cooling; another part of the air leaks into the exhaust channel through the sealing structure 8 between the combustion chamber test piece and the test section; in addition, a very small amount of air leaks into the external combustion cylinder 2 through the manufacturing tolerances of the air cavity 3 wall. This complex flow distribution and system leakage make it impossible to ensure that the air flow entering the combustion chamber head 4 to participate in combustion during the test is consistent with the overall machine design operating point.

[0031] To address the challenge of accurately obtaining system-level flow distribution characteristics during full-scale combustion chamber testing of heavy-duty gas turbines due to the complexity of the test system structure and sealing leaks, this invention proposes a combustion chamber test flow measurement method, system, electronic equipment, and storage medium. This invention not only verifies the machining and design compliance of each cooling structure within the combustion chamber test piece, but also accurately quantifies the leakage in the sealing structure caused by the coupling effect between the test section and the combustion chamber test piece, as well as the leakage from air chamber 3 to combustion cylinder 2. This provides indispensable quantitative data for accurately determining the test operating point, ultimately ensuring that the aerodynamic and thermodynamic conditions entering the combustion chamber head are strictly consistent with the overall engine design conditions, significantly improving the reliability and engineering guidance value of the full-scale test results.

[0032] According to a first aspect of the present invention, a method for testing the flow rate in a combustion chamber is provided, see reference. Figure 2 As shown, the testing method includes the following steps: S1. Independently measure the flow characteristics of the cooling structure on the transition section of the combustion chamber test piece to obtain its reference effective area; S2. On the assembled test section, perform the first system measurement to obtain the first total effective area including all leakage paths; S3. On the test section, after eliminating the influence of air cavity leakage through pressure control, a second system measurement is performed to obtain the second total effective area; S4. Based on the reference effective area, the first total effective area and the second total effective area, calculate the air cavity leakage area and the transition section rear seal leakage area by difference calculation. S5. Calculate the total intake flow rate of the test section based on the air cavity leakage area, the transition section rear seal leakage area, the reference effective area, and the overall machine design parameters, and formulate test conditions accordingly.

[0033] In one specific embodiment of the present invention, step S1 targets the cooling holes in the transition section and the rear mounting edge of the combustion chamber test piece. It should be understood that these cooling structures are necessary due to the extremely high ambient temperature inside the combustion chamber. Furthermore, the transition section is externally covered with a flow guide bushing and has instrument leads, resulting in a complex structure. Given that the effective area of ​​these two parts is an inherent structural characteristic of the combustion chamber test piece and is independent of the test section installation, to obtain higher measurement accuracy, the flow characteristics are independently measured using a dedicated flow testing fixture before the combustion chamber test piece leaves the factory. Specifically, the measurement method in this step is as follows: See Figure 3As shown, a dedicated flow testing fixture 11 is used, and the transition section 6 test piece is installed inside this fixture. The flow testing fixture 11 has an inlet and an outlet, the structure of which matches the outlet of the transition section 6 test piece and ensures a reliable sealing connection. The inlet of the transition section 6 test piece is sealed inside the flow testing fixture 11 by a transition section blocking plate 12. Thus, the pressurized gas introduced from the inlet of the flow testing fixture 11 first fills the fixture cavity, then flows into the internal flow channel of the transition section through the cooling hole structure, and finally is discharged to the atmosphere through the outlet of the transition section and the sealed outlet of the flow testing fixture 11. This arrangement ensures that the mass flow rate of all introduced gas flows through the cooling hole under test, providing a basis for accurately measuring its effective flow area. During measurement, a segmented isolation method was adopted: when it was necessary to test the effective area of ​​the transition section cooling hole 9, industrial tape was used to wrap and seal the rear-mounted side cooling hole 10; when it was necessary to test the effective area of ​​the rear-mounted side cooling hole 10, the transition section cooling hole 9 was wrapped and sealed. After wrapping and sealing, a soapy water leak test was performed at the maximum test pressure to confirm that there was no leakage in the sealed part, so as to ensure the independence and accuracy of the measurement. Subsequently, pressurized gas was supplied to the air inlet of the flow testing fixture 11, and the air mass flow rate at the air inlet of the fixture was measured. Absolute pressure P in and intake air temperature T, based on absolute pressure P in The differential pressure ∆p is calculated between the outlet ambient atmospheric pressure and the absolute pressure P. in The intake density ρ is calculated using the ideal gas law based on the intake temperature T. The effective area of ​​the corresponding measurement section is then calculated using the following formula. In this embodiment, the air pressure adjustment range of the inlet of the flow testing fixture 11 is 1.0~1.5 bar. Within this range, several operating points are selected at equal intervals for measurement. Based on the measurement data of all operating points, a pressure ratio (i.e., the ratio of inlet absolute pressure to atmospheric pressure) - mass flow rate relationship curve is plotted, and the data points are fitted. The accurate mass flow rate value corresponding to the design pressure ratio is obtained through this fitted curve, and the final effective area CdA of the corresponding measurement section is calculated accordingly.

[0034] Through the above-described distribution isolation and measurement process, the effective areas of the transition section cooling holes 9 and the rear mounting edge cooling holes 10 can be obtained respectively. The measured effective areas are compared with the design values ​​to verify the accuracy of the transition section test piece manufacturing. Preferably, when the deviation between the measured effective area and the design value does not exceed 5%, the manufacturing is considered accurate.

[0035] In one specific embodiment of the present invention, step S2 aims to obtain the first total effective area of ​​the combustion chamber test piece through system measurement. This first total effective area is one of the reference data for calculating the installation leakage area in subsequent calculations, and its measurement must be performed on the assembled test section to cover all possible leakage paths. The specific operation is as follows: See Figure 4 As shown, the combustion chamber head 4 is removed, and an end-face blocking plate 14 is installed at its installation position to completely seal the head flow channel. Then, an elastic ball 15 is inserted into the inlet of the transition section 6. The elastic ball 15 is preferably made of rubber and has good deformation capacity. By filling it with appropriate pressure, it is made to have an interference fit with the inner wall of the transition section 6 and form a tight seal, thereby ensuring good sealing and fixed position under the maximum test pressure. The exhaust passage of the test section is kept open, so that its outlet is connected to the atmospheric environment. At this time, since the combustion chamber head 4 and the inlet of the transition section 6 are blocked, all the air that enters can only flow out through other paths. The first total effective area is the sum of the effective area of ​​the air cavity leakage, the effective area of ​​the transition section cooling holes, the effective area of ​​the rear installation side cooling holes, and the effective area of ​​the transition section rear seal leakage, i.e. in, The first total effective area, The air leakage area is the area of ​​the air cavity. The effective area of ​​the cooling holes in the transition section. This refers to the effective area of ​​the rear-mounted side cooling holes. This refers to the effective area for sealing and leak prevention after the transition section.

[0036] Air at different pressures was introduced into the test section at the inlet, and the total air mass flow rate introduced into the test section was measured at different times. 1. Absolute pressure P of the import in In this embodiment, the inlet air pressure of the test section is controlled within a range of 1.0-1.5 bar. Several operating points are selected at equal intervals within this range for measurement. Based on the measurement data from all operating points, a pressure ratio-mass flow rate relationship curve of the system is plotted, and the precise mass flow rate value corresponding to the design pressure ratio is obtained from the fitted curve through data fitting. The corresponding P... in Calculate the air density ρ and differential pressure Δp with T, and calculate the first total effective area under this state using the same formula as in step S1. In this embodiment, a high-precision mass flow meter is installed in series in the upstream pipeline of the test section inlet, which can directly and accurately measure the mass flow rate of the gas passing through the pipeline.

[0037] In a specific embodiment of the present invention, step S3 aims to eliminate the influence of air cavity leakage on the measurement results by establishing a zero pressure difference condition between the combustion cylinder 2 and the air cavity 3, thereby obtaining the sum of the effective areas of the transition section cooling hole 9, the rear mounting edge cooling hole 10, and the transition section rear seal. The specific operation is as follows: The test is conducted under the condition that the test state in step S2 remains unchanged, namely, the combustion chamber head 4 is sealed by the end face blocking plate 14, the inlet of the transition section 6 is isolated and sealed by the elastic ball 15, and the exhaust passage of the test section is connected to the atmosphere. The pressure difference between the combustion cylinder 2 and the air chamber 3 is stabilized to zero by the following closed-loop control method: a differential pressure measuring point is set in the combustion cylinder 2, and the pressure in the air chamber 3 is used as the measurement reference; during the test, while maintaining normal ventilation in the air chamber 3, control gas is introduced into the combustion cylinder 2 through an independent pipeline, and the amount of gas introduced is adjusted in real time according to the reading of the differential pressure measuring point to stabilize the differential pressure reading to zero, thereby eliminating the leakage from the air chamber 3 to the combustion cylinder 2. After the zero pressure difference condition is established and stabilized, the test is repeated at the same inlet pressure condition used in step S2. Under this condition, since there is no pressure difference between the air chamber 3 and the combustion cylinder 2 that would cause a driving leakage, the leakage gas volume from the air chamber 3 to the combustion cylinder 2 is zero. At this time, the mass flow rate of the air introduced from the inlet of the test section is measured again. 2. Simultaneously record the inlet absolute pressure Pin and inlet temperature T. Based on the measurement data from several operating points, plot the pressure ratio-mass flow rate relationship curve and fit it to obtain the accurate flow rate value under the design pressure ratio. Use the corresponding P in Calculate the air density ρ and differential pressure Δp with T, and obtain the second total effective area using the same formula as in step S1. Second effective area It is the sum of the effective area of ​​the cooling holes in the transition section, the effective area of ​​the cooling holes on the rear mounting edge, and the effective area of ​​the rear seal leakage in the transition section, i.e. in, This is the second total effective area.

[0038] In a specific embodiment of the present invention, step S4 aims to calculate, based on the measurement results of the foregoing steps, two key leakage areas caused by the installation assembly: the air cavity leakage area and the transition section post-seal leakage area, through a difference calculation chain. The specific calculation method is as follows: Based on the fundamental principles of fluid mechanics and the law of conservation of mass, the only variable in the two system measurements is the opening and closing of the air cavity leakage path. Therefore, the difference is the effective leakage area of ​​the air cavity. The formula for calculating the effective leakage area of ​​the air cavity is as follows: in, The first total effective area, which includes all leakage paths, obtained in step S2. This is the second total effective area obtained in step S3 after eliminating the effects of air cavity leakage.

[0039] In obtaining the effective area of ​​air cavity leakage Based on this, the effective area of ​​the seal after the transition section is obtained by quadratic interpolation calculation, and the calculation formula is as follows: in, and This refers to the verified baseline effective area obtained through independent measurement of flow characteristics in step S1.

[0040] The difference calculation chain established in this step separates and precisely quantifies two installation leakage areas that cannot be directly measured and are crucial for determining test conditions from the complex total system measurements.

[0041] In one specific embodiment of the present invention, step S5 aims to integrate all acquired effective area data, calculate the total intake flow rate required for the test section based on the principle of overall engine equivalence, and formulate the final test conditions accordingly to perform a real and effective full-size performance verification of the combustion chamber. The specific calculation method is as follows: Given the inherent differences between the full-scale combustion chamber test bench structure and a real gas turbine, especially the effective leakage area of ​​the rear seal of the test section. The values ​​are not equal to the design values ​​under the overall engine environment. Therefore, to ensure that the aerodynamic and thermodynamic state of the combustion chamber head 4 in the test is strictly consistent with the overall engine design conditions, the total intake flow rate of the test section must be specifically modified. The total intake flow rate is calculated based on the following formula. in, The total mass flow rate of air that needs to be introduced into the test section inlet to reproduce the head environment of the entire machine during full-scale testing; This refers to the total mass flow rate of air entering the combustion chamber at the design operating point in the overall machine environment. The effective area of ​​the combustion chamber test piece itself includes, but is not limited to, the head flow area and the area of ​​the cooling holes in the transition section. and the area of ​​the cooling holes on the mounting side The value is the sum of the effective areas of all components; and The leak area of ​​the test system calculated in step S4 is respectively the installation area of ​​the test system. This is the effective leakage area of ​​the combustion chamber rear seal, given in the overall design of the gas turbine. This value is a known design input condition.

[0042] By adjusting the total mass flow rate into the test section To compensate for the flow distribution deviation caused by differences in sealing and other structural features between the test bench and the complete engine, thus ensuring that the core air flow rate entering the combustion chamber head 4 for combustion is equal in both the "full-size test bench environment" and the "real gas turbine engine environment". This is based on calculations... This allows for the development of precise test conditions, including but not limited to parameters such as inlet airflow, pressure, and temperature. During full-scale combustion chamber testing, air and fuel are supplied to the test section according to these conditions, enabling effective and reliable verification of the combustion chamber's ignition performance, flameout boundary, combustion stability, and emission characteristics.

[0043] According to a second aspect of the present invention, a combustion chamber test flow rate testing system is proposed to implement the above-mentioned method for testing combustion chamber test flow rate. (See also...) Figure 5 As shown, the system integrates hardware devices, sensors, actuators, and computing software. It mainly includes a flow testing fixture, a full-size test section module, a sensor module, a pressure control module, a data acquisition and control module, and a data processing and calculation module. The sensor modules are deployed on the full-size test section module and the flow testing fixture. The data acquisition and control module is connected to all sensors and the pressure control module via cables. The data processing and calculation module receives raw data from the data acquisition and control module. All modules work collaboratively to accurately acquire the flow distribution characteristics of the test system and the combustion chamber test piece.

[0044] The flow testing fixture is an independent device that provides pre-shipment flow characteristic measurements for combustion chamber test pieces. It offers a sealed and controllable testing environment, where the transition section test piece is installed and its inlet is sealed with a blocking plate, ensuring that airflow can only exit from the cooling holes under test. By controlling the pressure at the inlet of the flow testing fixture and measuring the air mass flow rate, the reference effective area of ​​key components of the combustion chamber test piece is obtained.

[0045] The full-scale test section module is the core hardware platform for simulating a real gas turbine environment and performing system-level measurements. Its function is to reproduce the entire machine structure, including the intake diffuser, air chamber, and combustion cylinder, and to provide an installation interface for the combustion chamber test piece. It also includes sealing devices such as end face blocking plates and elastic balls necessary for implementing the method of this invention. The sealing devices can seal the combustion chamber head and transition section inlet respectively, isolating different airflow paths during the test, which is the physical basis for realizing the measurement.

[0046] The sensor module includes pressure sensors located at the inlet of the full-size test section, the air chamber, the combustion cylinder, and the inlet of the flow test fixture, used to measure the absolute pressure and differential pressure of the gas; a temperature sensor for measuring the inlet air temperature, providing parameters for calculating air density; and a high-precision mass flow meter connected in series on the main inlet pipeline of the full-size test section, used to directly measure the mass flow rate of the air entering the full-size test section module.

[0047] The pressure control module is the actuator that realizes zero pressure difference control between the combustion cylinder and the air chamber. Its function is to receive pressure signals from the two chambers and drive the pressure regulating valve connected to the combustion cylinder to charge or exhaust in real time through the built-in closed-loop control algorithm, thereby dynamically maintaining the pressure difference between the two chambers at zero.

[0048] The data acquisition and control module communicates with all sensors via multiple bus protocols to achieve synchronous, high-speed, and high-precision acquisition of multi-channel data. It is also responsible for sending control commands to the pressure control module, driving it to perform automatic pressure regulation and controlling the total pressure at the test section inlet. Furthermore, a human-machine interface is provided, enabling operators to set test sequences, monitor real-time status, and intervene in critical operations.

[0049] The data processing and calculation module can perform curve fitting on the collected pressure ratio-flow rate data and, based on the formula... The effective areas of the transition section cooling holes and the rear mounting edge cooling holes, as well as the first total effective area and the second total effective area, are calculated. Simultaneously, the effective areas of the transition section cooling holes and the rear mounting edge cooling holes, obtained through independent flow characteristic measurements, are used. Combined with the first total effective area and the second total effective area, a difference calculation chain is executed to calculate the air cavity leakage area and the transition section rear seal leakage area. Finally, based on the principle of overall system equivalence, the total effective area of ​​the combustion chamber test piece, the air cavity leakage area, the transition section rear seal leakage area, and the overall system design parameters are integrated to complete the calculation of the total air intake of the test section, providing a quantitative basis for determining the final test conditions.

[0050] According to a third aspect of the present invention, a computer program product comprising a computer program is provided.

[0051] Figure 6 A schematic block diagram of a computer system architecture for implementing an electronic device according to embodiments of the present application is shown.

[0052] It should be noted that, Figure 6 The computer system 600 of the electronic device shown is merely an example and should not impose any limitation on the functionality and scope of use of the embodiments of this application.

[0053] like Figure 6As shown, the computer system 600 includes a central processing unit (CPU) 601, which can perform various appropriate actions and processes based on programs stored in read-only memory (ROM) 602 or programs loaded from storage section 608 into random access memory (RAM). The RAM 603 also stores various programs and data required for system operation. The CPU 601, ROM 602, and RAM 603 are interconnected via a bus 604. An input / output interface 605 (I / O interface) is also connected to the bus 604.

[0054] The following components are connected to the input / output interface 605: an input section 606 including a keyboard, mouse, etc.; an output section 607 including a cathode ray tube (CRT), liquid crystal display (LCD), etc., and speakers, etc.; a storage section 608 including a hard disk, etc.; and a communication section 609 including a network interface card such as a local area network card, modem, etc. The communication section 609 performs communication processing via a network such as the Internet. A drive 610 is also connected to the input / output interface 605 as needed. A removable medium 33, such as a disk, optical disk, magneto-optical disk, semiconductor memory, etc., is installed on the drive 610 as needed so that computer programs read from it can be installed into the storage section 608 as needed.

[0055] Specifically, according to embodiments of this application, the processes described in the various method flowcharts can be implemented as computer software programs. For example, embodiments of this application include a computer program product comprising a computer program carried on a computer-readable medium, the computer program containing program code for performing the methods shown in the flowcharts. In such embodiments, the computer program can be downloaded and installed from a network via communication section 609, and / or installed from a removable medium. When the computer program is executed by central processing unit 601, it performs various functions defined in the system of this application.

[0056] According to a fourth aspect of this application, an electronic device is also provided. This embodiment will be described using this electronic device as an example of a terminal device. Figure 7 As shown, the electronic device includes a memory 702 and a processor 704. The memory 702 stores a computer program, and the processor 704 is configured to execute the data processing and calculation steps in the combustion chamber test flow test method described above through the computer program.

[0057] Optionally, in this embodiment, the aforementioned electronic device may be located in at least one of a plurality of network devices in a computer network.

[0058] Alternatively, as those skilled in the art will understand, Figure 7 The structure shown is for illustrative purposes only. Figure 7 This does not limit the structure of the aforementioned electronic devices. For example, the electronic device may also include components that are more... Figure 7 The more or fewer components shown (such as network interfaces, etc.), or having the same Figure 7 The different configurations shown.

[0059] The memory 702 can be used to store software programs and modules, such as the program instructions / modules corresponding to the data processing and calculation steps in the combustion chamber test flow test method in this embodiment. The processor 704 executes various functional applications and data processing by running the software programs and modules stored in the memory 702. The memory 702 may include high-speed random access memory, and may also include non-volatile memory, such as one or more magnetic storage devices, flash memory, or other non-volatile solid-state memory. Specifically, the memory 702 may be used, but is not limited to, storing collected test data, flow parameters, and processing results. As an example, such as... Figure 7 As shown, the memory 702 may include, but is not limited to, the data processing and calculation module of the combustion chamber test flow test system described above. Furthermore, it may include, but is not limited to, other module units in the aforementioned device, which will not be elaborated upon in this example.

[0060] Optionally, the transmission device 706 described above is used to receive or send data via a network. Specific examples of the network described above may include wired networks and wireless networks.

[0061] In addition, the aforementioned electronic device also includes: a display 708 for displaying the aforementioned test data and processing results; and a connection bus 710 for connecting the various module components in the aforementioned electronic device.

[0062] According to a fifth aspect of this application, a computer-readable storage medium is provided, wherein a processor of an electronic device reads computer instructions from the computer-readable storage medium and executes the computer instructions, causing the electronic device to perform the data processing and calculation steps in the above-described combustion chamber test flow test method.

[0063] Optionally, in this embodiment, those skilled in the art will understand that all or part of the steps in the various methods of the above embodiments can be implemented by a program instructing the hardware related to the terminal device. The program can be stored in a computer-readable storage medium, which may include: flash drive, read-only memory (ROM), random access memory (RAM), disk or optical disk, etc.

[0064] By applying the above-described technical solution of the present invention, at least the following technical effects are achieved: 1. This invention systematically proposes and solves the problem of flow distribution under the coupling effect of "test system" and "test piece" in full-scale testing of heavy-duty gas turbines. It can not only verify the processing conformity of the test piece body, but also accurately quantify system-level leaks such as "air cavity leakage" and "transition section post-seal leakage" caused by installation and assembly, filling the gap in the existing technology in this field.

[0065] 2. This invention proposes a complete technical chain of "independent measurement - system measurement - difference calculation - operating condition formulation" to ensure the accuracy of test conditions and the validity of results. It accurately quantifies installation leaks that cannot be directly measured and calculates the total flow rate of the test section that can truly reproduce the head environment through the "equivalent conversion formula between the whole machine and the test bench," fundamentally ensuring that the test results can effectively characterize the overall machine's operating status.

[0066] 3. This invention does not depend on a specific model of test section or test piece structure. The "step-by-step isolation measurement" principle for complex cooling and sealing structures, the leakage elimination method based on differential pressure control, and the logic of system-level flow distribution characteristics described herein can be universally applied to full-scale tests of combustion chambers of heavy-duty gas turbines with various similar structures, establishing a clear, reliable, and reusable technical template for the test process in this field.

[0067] 4. This invention combines high-precision sensor measurement, closed-loop control, and highly operable manual blocking, ensuring the accuracy of key data measurement while avoiding extremely complex and expensive permanent modifications to the test section, significantly reducing test complexity and cost, and has outstanding engineering application value.

[0068] The above are merely several specific embodiments of the present invention, but the scope of protection of the present invention is not limited thereto. Any equivalent substitutions or modifications made by those skilled in the art within the scope of the technology disclosed in the present invention, based on the technical solution and inventive concept of the present invention, should be covered within the scope of protection of the present invention.

[0069] It should be noted that, in this document, relational terms such as "first" and "second" are used merely to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes the element.

[0070] It should be noted that, in the description of this specification, the references to terms such as "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of this application. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. Moreover, without contradiction, those skilled in the art can combine and integrate the different embodiments or examples described in this specification, as well as the features of different embodiments or examples.

Claims

1. A method for testing the flow rate in a combustion chamber, characterized in that, The method includes the following steps: S1. Independently measure the flow characteristics of the cooling structure of the transition section of the combustion chamber test piece to obtain its reference effective area; S2. On the assembled test section, perform the first system measurement to obtain the first total effective area including all leakage paths; S3. On the test section, after eliminating the influence of air cavity leakage through pressure control, a second system measurement is performed to obtain the second total effective area; S4. Based on the reference effective area, the first total effective area and the second total effective area, calculate the air cavity leakage area and the transition section post-seal leakage area; S5. Calculate the total intake flow rate of the test section based on the air cavity leakage area, the transition section rear seal leakage area, the reference effective area, and the overall machine design parameters, and formulate test conditions accordingly.

2. The combustion chamber test flow rate test method according to claim 1, characterized in that, In step S1, a blocking and isolation measurement method is adopted. By blocking part of the cooling structure while keeping the rest of the cooling structure open, the effective area of ​​each part of the cooling structure is measured in stages.

3. The combustion chamber test flow rate test method according to claim 2, characterized in that, In step S1, the reference effective area includes the effective area of ​​the cooling holes in the transition section and the effective area of ​​the cooling holes in the rear mounting edge.

4. The combustion chamber test flow rate test method according to claim 3, characterized in that, In step S1, the reference effective area is calculated using the following formula. Where CdA is the effective area of ​​the unblocked cooling hole. ρ is the air mass flow rate, ρ is the inlet air density, and ∆p is the pressure difference between the pressure measuring point at the inlet of the flow test fixture and the atmospheric pressure at the outlet.

5. The combustion chamber test flow rate test method according to claim 1, characterized in that: The first system measurement includes: sealing the head flow channel and transition section inlet of the combustion chamber test piece, introducing air at different pressures into the test section inlet, and measuring the total mass flow rate to obtain the first total effective area.

6. The combustion chamber test flow rate test method according to claim 5, characterized in that: The first total effective area is the sum of the effective area of ​​air cavity leakage, the effective area of ​​transition section cooling holes, the effective area of ​​rear mounting edge cooling holes, and the effective area of ​​transition section rear seal.

7. The combustion chamber test flow rate test method according to claim 5, characterized in that: The head flow channel of the combustion chamber test piece is sealed with an end face blocking plate, and the inlet of the transition section is sealed with an elastic ball.

8. The combustion chamber test flow rate test method according to claim 1, characterized in that: The second system measurement includes: maintaining the blocked state of the first system measurement, using closed-loop control to keep the pressure in the combustion cylinder consistent with the pressure in the air chamber to eliminate the pressure difference between them; introducing air at different pressures into the test section inlet and measuring the total mass flow rate to obtain the second total effective area.

9. The combustion chamber test flow rate test method according to claim 8, characterized in that: The second total effective area is the sum of the effective area of ​​the cooling holes in the transition section, the effective area of ​​the cooling holes on the rear mounting edge, and the effective area of ​​the rear seal of the transition section.

10. The combustion chamber test flow rate test method according to claim 1, characterized in that, Step S4 includes: The air cavity leakage area is calculated based on the first total effective area measured in step S2 and the second total effective area measured in step S3, using the following formula: in, The first total effective area, This is the second total effective area; Based on the above calculation results and the reference effective area measured in step S1 and the second total effective area measured in step S2, the leakage area of ​​the seal after the transition section is calculated. The calculation formula is as follows: in, This is the second total effective area. The area of ​​the cooling holes in the transition section. This refers to the area of ​​the cooling holes on the rear-mounted side.

11. The combustion chamber test flow rate test method according to claim 10, characterized in that: The formula for calculating the total intake flow rate of the test section is as follows: in, This represents the total mass flow rate of air introduced into the test section at the inlet. This refers to the total mass flow rate of air entering the combustion chamber at the design operating point in the overall machine environment. It is the sum of the flow area at the head of the combustion chamber test piece, the area of ​​the cooling holes in the transition section, and the area of ​​the cooling holes at the rear mounting edge; This refers to the effective leakage area of ​​the combustion chamber rear seal in the overall design of a gas turbine.

12. A combustion chamber test flow rate testing system, used to implement the method as described in any one of claims 1 to 11, characterized in that, The system includes: The flow testing fixture module is used for offline flow calibration of combustion chamber test specimens; A full-size test section module is used to simulate the overall machine environment and install the combustion chamber test piece; The sensor module, deployed on the flow testing fixture module and the full-size test section module, is used to measure pressure, temperature and mass flow rate; The pressure control module is used to control the pressure difference between the combustion cylinder and the air chamber in the full-size test section module; A data acquisition and control module, connected to the sensor module and the pressure control module, is used to acquire data and send control commands. The data processing and calculation module, connected to the data acquisition and control module, is used to execute the calculation logic of the method and output the final result.

13. A computer program product, comprising a computer program, characterized in that, When executed by a processor, the computer program performs the data processing and calculation steps in the combustion chamber test flow test method according to any one of claims 1 to 11.

14. An electronic device comprising a memory and a processor, characterized in that, The memory stores a computer program, and the processor is configured to execute the data processing and calculation steps in the combustion chamber test flow test method according to any one of claims 1 to 11 through the computer program.

15. A computer-readable storage medium, characterized in that, The computer-readable storage medium includes a stored computer program, wherein the computer program can be executed by an electronic device to perform the data processing and calculation steps in the combustion chamber test flow test method according to any one of claims 1 to 11.

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