A method for detecting inlet flow of a turbine component transition state test

Abstract

A kind of turbine component transition state test import flow detection method, design utilizes the steady total pressure of turbine import before transition state starts, dynamic total pressure, the steady static pressure of turbine import before transition state starts, dynamic static pressure, and the dynamic total pressure of turbine import at time under transition state, dynamic static pressure, the corrected total pressure of turbine import at time under transition state, corrected static pressure are calculated to obtain, and then the Mach number of turbine import at time under transition state, flow coefficient are calculated, combined with the steady flow of turbine import before transition state starts, the steady flow of turbine import after transition state terminates, the conversion flow coefficient of turbine import before transition state starts, after transition state terminates is calculated, the flow coefficient of turbine import at time is calculated by steady dynamic mapping interpolation, finally the flow of turbine import at time is calculated.

Description

Technical Field

[0001] This application belongs to the field of turbine component transient state test inlet flow measurement technology, specifically relating to a method for detecting turbine component transient state test inlet flow. Background Technology

[0002] Turbines are the core hot-end components of aero engines and gas turbines. The internal flow, heat transfer, and geometry changes during the transition state are extremely complex, making them the part facing the highest risks.

[0003] Conducting transient state tests on turbine components can directly obtain effective data on changes in aerodynamic, thermodynamic, and structural parameters during the turbine's transient state, which can be used to support the matching design of aero engines and gas turbines.

[0004] In the transient state test of turbine components, the measurement of turbine inlet flow rate is involved. Currently, this is mostly done using orifice plate flow meters or venturi tubes. However, these technical solutions have the following drawbacks:

[0005] In the transition state, the turbine inlet flow field has instantaneous characteristics, and measuring the turbine inlet flow with orifice flowmeters or venturi tubes requires a long settling time, making it difficult to accurately measure the turbine inlet flow.

[0006] This application is made in view of the aforementioned technical deficiencies.

[0007] It should be noted that the above background information is only used to assist in understanding the inventive concept and technical solution of this application, and it does not necessarily belong to the prior art of this patent application. In the absence of clear evidence that the above information was disclosed on the filing date of this application, the above background information should not be used to evaluate the novelty and inventiveness of this application. Summary of the Invention

[0008] The purpose of this application is to provide a method for detecting the inlet flow rate of a turbine component during transition state testing, so as to overcome or mitigate at least one of the known technical defects.

[0009] The technical solution of this application is:

[0010] A method for detecting inlet flow rate during transient testing of turbine components includes:

[0011] Calculate the turbine inlet under transient state. Total corrected pressure at any time ,in: The steady-state total pressure at the turbine inlet before the transition state begins; For the turbine inlet in the transition state The dynamic total pressure at any given moment; The dynamic total pressure at the turbine inlet before the transition state begins;

[0012] Calculate the turbine inlet under transient state. Time-corrected static pressure ,in: The steady-state static pressure at the turbine inlet before the transition state begins; For the turbine inlet in the transition state Dynamic static pressure at any given moment; The dynamic static pressure at the turbine inlet before the transition state begins;

[0013] Calculate the turbine inlet under transient state. Mach number at time ,in, The turbine airflow adiabatic index;

[0014] Calculate the turbine inlet under transient state. Flow coefficient at time ;

[0015] Calculate the equivalent flow coefficient of the turbine inlet before the start of the transient state. ,in, Steady-state flow rate at the turbine inlet before the transition state begins; The flow coefficient at the turbine inlet before the transition state begins;

[0016] Calculate the equivalent flow coefficient of the turbine inlet after the transient state terminates. ,in, Steady-state flow rate at the turbine inlet after the transition state terminates; The flow coefficient at the turbine inlet after the transition state terminates;

[0017] Calculate the turbine inlet under transient state. Conversion flow coefficient at time ;

[0018] Calculate the turbine inlet under transient state. Flow of time .

[0019] According to at least one embodiment of this application, in the above-described method for detecting the inlet flow rate of a turbine component during transition state testing, , , The total pressure is obtained by setting steady-state total pressure measurement points and dynamic total pressure measurement points within the turbine inlet measurement section, and averaging the measurements taken by steady-state total pressure probe and dynamic total pressure probe. The steady-state total pressure measurement points and dynamic total pressure measurement points are arranged at intervals in the circumferential direction and distributed along the same annular surface in the radial direction, with a distance of no more than 10 mm between adjacent measurement points.

[0020] , , The static pressure is obtained by setting steady-state static pressure measuring points and dynamic static pressure measuring points inside and outside the turbine inlet measuring section, and averaging the measurements taken by steady-state total pressure probe and dynamic total pressure probe. The steady-state static pressure measuring points and dynamic static pressure measuring points are arranged at intervals in the circumferential direction, and the number is consistent and not less than 8.

[0021] According to at least one embodiment of this application, in the above-described method for detecting the inlet flow rate of a turbine component during transition state testing, , The flow rate is measured using a flow measurement device located at the turbine inlet. Attached Figure Description

[0022] Figure 1 This is a schematic diagram of total pressure measured by a steady-state total pressure probe and a dynamic total pressure probe within the turbine inlet measurement section, as provided in the embodiments of this application.

[0023] Figure 2 This is a schematic diagram provided in this application embodiment, showing that steady-state static pressure measuring points and dynamic static pressure measuring points are set in the inner and outer casings of the turbine inlet measuring section, and static pressure is measured by steady-state total pressure probe and dynamic total pressure probe;

[0024] Figure 3 This is a schematic diagram illustrating the parameter changes and timing definitions at the inlet of the turbine component during the transition state test, provided in an embodiment of this application.

[0025] Figure 4 This is a schematic diagram of the turbine component transition state test inlet flow detection method provided in the embodiments of this application.

[0026] To better illustrate this embodiment, some parts in the accompanying drawings may be omitted, enlarged, or reduced, and do not represent the actual size of the product. Furthermore, the accompanying drawings are for illustrative purposes only and should not be construed as limiting this patent. Detailed Implementation

[0027] To make the technical solution and advantages of this application clearer, the technical solution of this application will be described in a clearer and more complete manner below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are only some embodiments of this application, and are only used to explain this application, not to limit this application. It should be noted that, for ease of description, only the parts related to this application are shown in the accompanying drawings. Other related parts can be referred to the general design. In the absence of conflict, the embodiments and technical features in the embodiments of this application can be combined with each other to obtain new embodiments.

[0028] Furthermore, unless otherwise defined, the technical or scientific terms used in this application description shall have the ordinary meaning understood by one of ordinary skill in the art to which this application pertains. The terms "upper," "lower," "left," "right," "center," "vertical," "horizontal," "inner," and "outer," etc., used in this application description to indicate relative direction or positional relationship are used only to indicate relative orientation or positional relationship, and do not imply that the device or component must have a specific orientation, or be constructed and operated in a specific orientation. When the absolute position of the described object changes, its relative positional relationship may also change accordingly, and therefore should not be construed as a limitation on this application. The terms "first," "second," "third," and similar terms used in this application description are used only for descriptive purposes to distinguish different components, and should not be construed as indicating or implying relative importance. The terms "a," "one," or "the," etc., used in this application description should not be construed as an absolute limitation on quantity, but should be construed as indicating the existence of at least one. The terms "including," "comprising," etc., used in this application description mean that the element or object preceding the word covers the element or object listed after the word and its equivalents, without excluding other elements or objects.

[0029] Furthermore, it should be noted that, unless otherwise explicitly specified and limited, terms such as “installation,” “connection,” and “linkage” used in the description of this application should be interpreted broadly. For example, a connection can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium; or it can be a connection within two components. Those skilled in the art can understand its specific meaning in this application according to the specific circumstances.

[0030] The following is in conjunction with the appendix Figures 1 to 2 This application will be described in further detail.

[0031] A method for detecting inlet flow rate during transient testing of turbine components includes:

[0032] Calculate the turbine inlet under transient state. Total corrected pressure at any time ,in: This is the steady-state total pressure at the turbine inlet before the transition state begins, which is also the steady-state total pressure at the turbine inlet at the very beginning of the transition state. For the turbine inlet in the transition state The dynamic total pressure at any given moment; The dynamic total pressure at the turbine inlet before the transition state begins, that is, the dynamic total pressure at the turbine inlet at the very beginning of the transition state;

[0033] Calculate the turbine inlet under transient state. Time-corrected static pressure ,in: This refers to the steady-state static pressure at the turbine inlet before the transition state begins, which is also the steady-state static pressure at the turbine inlet at the very beginning of the transition state. For the turbine inlet in the transition state Dynamic static pressure at any given moment; The dynamic static pressure at the turbine inlet before the transition state begins, that is, the dynamic static pressure at the turbine inlet at the very beginning of the transition state.

[0034] Calculate the turbine inlet under transient state. Mach number at time ,in, The turbine airflow adiabatic index;

[0035] Calculate the turbine inlet under transient state. Flow coefficient at time ;

[0036] Calculate the equivalent flow coefficient of the turbine inlet before the start of the transient state. ,in, The steady-state flow rate at the turbine inlet before the transition state begins, that is, the steady-state flow rate at the turbine inlet when the transition state just begins. The flow coefficient at the turbine inlet before the transition state begins can be referenced. Perform calculations;

[0037] Calculate the equivalent flow coefficient of the turbine inlet after the transient state terminates. ,in, The steady-state flow rate at the turbine inlet after the transition state ends, i.e., the steady-state flow rate at the turbine inlet after the transition state ends. The flow coefficient at the turbine inlet after the transition state terminates can be referenced. Perform calculations;

[0038] Calculate the turbine inlet under transient state. Conversion flow coefficient at time ;

[0039] Calculate the turbine inlet under transient state. Flow of time .

[0040] Regarding the turbine component transient test inlet flow detection method disclosed in the above embodiments, those skilled in the art will understand that its design utilizes the easily measurable steady-state total pressure of the turbine inlet before the start of the transient state. Turbine inlet in transition state Dynamic total pressure at any moment Dynamic total pressure at the turbine inlet before the transition state begins Steady-state static pressure at the turbine inlet before the transition state begins Turbine inlet in transition state Dynamic static pressure at any moment Dynamic static pressure at the turbine inlet before the transition state begins The calculations show that the turbine inlet in the transition state is... Total corrected pressure at any time Corrected static pressure Furthermore, the turbine inlet under the transition state was calculated. Mach number at time Flow coefficient Combined with the steady-state flow rate at the turbine inlet before the transition state begins Steady-state flow rate at turbine inlet after transient termination The equivalent flow coefficient of the turbine inlet before the start of the transition state was calculated. And the equivalent flow coefficient of the turbine inlet after the transition state terminates. This allows for the calculation of the turbine inlet under the transient state through steady-state mapping interpolation. Flow coefficient at time Ultimately, it is possible to accurately calculate the turbine inlet under the transition state. Flow of time .

[0041] In some optional embodiments, in the above-described method for detecting the inlet flow rate during the transition state test of turbine components, , , The total pressure is obtained by setting steady-state and dynamic total pressure measurement points within the turbine inlet measurement section, and averaging the measurements taken by the steady-state and dynamic total pressure probes. The steady-state and dynamic total pressure measurement points are arranged at intervals in the circumferential direction and distributed along equal annular surfaces in the radial direction, with a distance of no more than 10 mm between adjacent measurement points. Figure 1 As shown;

[0042] , , The static pressure is obtained by setting steady-state and dynamic static pressure measuring points inside and outside the turbine inlet measuring section, and averaging the measurements taken by the steady-state total pressure probe and the dynamic total pressure probe. The steady-state and dynamic static pressure measuring points are arranged at intervals in the circumferential direction, and the number is consistent and not less than 8. Figure 2 As shown.

[0043] In some optional embodiments, in the above-described method for detecting the inlet flow rate during the transition state test of turbine components, , The flow rate is measured by a flow measurement device arranged at the turbine inlet.

[0044] The various embodiments in the specification are described in a progressive manner, with each embodiment focusing on the differences from other embodiments. The same or similar parts between the various embodiments can be referred to each other.

[0045] The technical solution of this application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of this application is obviously not limited to these specific embodiments. Without departing from the principles of this application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will all fall within the scope of protection of this application.

Claims

1. A method for detecting the inlet flow rate during a transient state test of a turbine component, characterized in that, include: Calculate the turbine inlet under transient state. Total corrected pressure at any time ,in: The steady-state total pressure at the turbine inlet before the transition state begins; For the turbine inlet in the transition state The dynamic total pressure at any given moment; The dynamic total pressure at the turbine inlet before the transition state begins; Calculate the turbine inlet under transient state. Time-corrected static pressure ,in: The steady-state static pressure at the turbine inlet before the transition state begins; For the turbine inlet in the transition state Dynamic static pressure at any given moment; The dynamic static pressure at the turbine inlet before the transition state begins; Calculate the turbine inlet under transient state. Mach number at time ,in, The turbine airflow adiabatic index; Calculate the turbine inlet under transient state. Flow coefficient at time ; Calculate the equivalent flow coefficient of the turbine inlet before the start of the transient state. ,in, Steady-state flow rate at the turbine inlet before the transition state begins; The flow coefficient at the turbine inlet before the transition state begins; Calculate the equivalent flow coefficient of the turbine inlet after the transient state terminates. ,in, Steady-state flow rate at the turbine inlet after the transition state terminates; The flow coefficient at the turbine inlet after the transition state terminates; Calculate the turbine inlet under transient state. Conversion flow coefficient at time ; Calculate the turbine inlet under transient state. Flow of time .

2. The method for detecting the inlet flow rate of a turbine component during transient testing according to claim 1, characterized in that, , , The total pressure is obtained by setting steady-state total pressure measurement points and dynamic total pressure measurement points within the turbine inlet measurement section, and averaging the measurements taken by steady-state total pressure probe and dynamic total pressure probe. The steady-state total pressure measurement points and dynamic total pressure measurement points are arranged at intervals in the circumferential direction and distributed along the same annular surface in the radial direction, with a distance of no more than 10 mm between adjacent measurement points. , , The static pressure is obtained by setting steady-state static pressure measuring points and dynamic static pressure measuring points inside and outside the turbine inlet measuring section, and averaging the measurements taken by steady-state total pressure probe and dynamic total pressure probe. The steady-state static pressure measuring points and dynamic static pressure measuring points are arranged at intervals in the circumferential direction, and the number is consistent and not less than 8.

3. The method for detecting the inlet flow rate of a turbine component during transient testing according to claim 1, characterized in that, , The flow rate is measured by a flow measurement device arranged at the turbine inlet.

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