CN112197826A - Air inlet mass flow measuring device and measuring method for aircraft engine - Google Patents
Air inlet mass flow measuring device and measuring method for aircraft engine Download PDFInfo
- Publication number
- CN112197826A CN112197826A CN202010907928.3A CN202010907928A CN112197826A CN 112197826 A CN112197826 A CN 112197826A CN 202010907928 A CN202010907928 A CN 202010907928A CN 112197826 A CN112197826 A CN 112197826A
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- mass flow
- pressure
- aircraft engine
- stabilizing section
- measuring device
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01F—MEASURING VOLUME, VOLUME FLOW, MASS FLOW OR LIQUID LEVEL; METERING BY VOLUME
- G01F1/00—Measuring the volume flow or mass flow of fluid or fluent solid material wherein the fluid passes through a meter in a continuous flow
- G01F1/76—Devices for measuring mass flow of a fluid or a fluent solid material
- G01F1/86—Indirect mass flowmeters, e.g. measuring volume flow and density, temperature or pressure
- G01F1/88—Indirect mass flowmeters, e.g. measuring volume flow and density, temperature or pressure with differential-pressure measurement to determine the volume flow
-
- 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
Abstract
The invention discloses an air inlet mass flow measuring device of an aircraft engine, which at least comprises an end surface guide plate, a horn nozzle, a pressure stabilizing section and an atmospheric pressure gauge for realizing atmospheric pressure measurement, wherein the guide plate is arranged on the outer edge of the horn nozzle and connected with the pressure stabilizing section, the contraction end of the horn nozzle is connected with the pressure stabilizing section, and the other end of the pressure stabilizing section is connected with an air inlet of the aircraft engine; a plurality of temperature sensors are uniformly arranged in the circumferential direction of the end face guide plate; the middle end side wall of the pressure stabilizing section is provided with an annular pipeline, a plurality of static pressure holes are circumferentially arranged on the annular pipeline, and a total pressure sensor is arranged in the annular pipeline. The measuring device disclosed by the invention can realize the quick and high-precision measurement of the air inlet mass flow of the engine on the premise of not influencing the working state of the engine, and has the advantages of simple measuring method and low cost.
Description
Technical Field
The invention belongs to the field of aero-engines, and particularly relates to an aero-engine air inlet mass flow measuring device and a measuring method.
Background
The aircraft engine is used for providing aircraft power, and when the aircraft engine is used, the air inlet mass flow of the engine in different working states needs to be obtained, so that traction indexes are provided for the design of an air inlet channel of the aircraft, and the air inlet requirements of the engine under different working conditions in a flight envelope are met.
For the demonstration and verification flight test of the active jet flow flight control technology, one scheme is to improve the air compressor of the aero-engine and bleed air from the back of the air compressor to provide compressed air required by jet flow flight control. For this case, detailed evaluation of the engine intake mass flow under different operating conditions is required to evaluate the safe bleed air mass flow boundary that the engine may provide.
Accordingly, there is a need to establish an aircraft engine intake mass flow measurement device that can be used to quickly measure engine intake mass flow.
Disclosure of Invention
The invention aims to overcome the defects of the prior art and provide the air inlet mass flow measuring device of the aircraft engine, so that the air inlet mass flow of the engine can be rapidly measured.
The purpose of the invention is realized by the following technical scheme:
the measuring device at least comprises an end surface guide plate, a horn nozzle, a pressure stabilizing section and an atmospheric pressure gauge for realizing atmospheric pressure measurement, wherein the guide plate is connected with the outer edge of the horn nozzle, the contraction end of the horn nozzle is connected with the pressure stabilizing section, and the other end of the pressure stabilizing section is connected with an air inlet of the aero-engine; a plurality of temperature sensors are uniformly arranged in the circumferential direction of the end face guide plate; the middle end side wall of the pressure stabilizing section is provided with an annular pipeline, a plurality of static pressure holes are circumferentially arranged on the annular pipeline, and a total pressure sensor is arranged in the annular pipeline.
According to a preferred embodiment, the bell-mouth has the shape of an AES bell-mouth standard shape, and the dimension L2 of the bell-mouth in the flow direction is the same as the diameter D of the surge section.
According to a preferred embodiment, the diameter D of the surge section is the same as the diameter of the air inlet of the aircraft engine; and the length L1 of the pressure stabilizing section is 1.2-1.5 times of the diameter D.
According to a preferred embodiment, the air inlet end of the trumpet nozzle is also provided with a filter screen.
According to a preferred embodiment, the diameter of the filter screen is larger than the outer diameter of the air inlet end of the bell mouth.
According to a preferred embodiment, the number of the temperature sensors arranged on the circumference of the end face guide plate is 6; the temperature sensor is a T-shaped temperature sensor.
According to a preferred embodiment, the annular duct is provided with 6 static vents in the circumferential direction.
According to a preferred embodiment, the total pressure sensor is a differential pressure transmitter for measuring the dynamic pressure of the gas flow in the surge section.
According to a preferred embodiment, the atmospheric pressure gauge is a mercury pressure gauge.
A method for measuring the air inlet mass flow of an aero-engine comprises the following steps:
wherein the content of the first and second substances,
the mass flow is shown as rho, the air density of the pressure stabilizing section is shown as v, the airflow flowing speed in the pressure stabilizing section is shown as v, and the flow area in the pressure stabilizing section is shown as A; wherein, the air density rho in the pressure stabilizing section is equal to P0/RT，P0Atmospheric pressure, R is a constant value, and T is the inlet air temperature; and, the flow velocity in the surge section
q is dynamic pressure.
The main scheme and the further selection schemes can be freely combined to form a plurality of schemes which are all adopted and claimed by the invention; in the invention, the selection (each non-conflict selection) and other selections can be freely combined. The skilled person in the art can understand that there are many combinations, which are all the technical solutions to be protected by the present invention, according to the prior art and the common general knowledge after understanding the scheme of the present invention, and the technical solutions are not exhaustive herein.
The invention has the beneficial effects that: the measuring device and the corresponding measuring method disclosed by the invention can realize the quick and high-precision measurement of the mass flow of the air inlet of the engine on the premise of not influencing the working state of the engine, and the measuring method is simple and has low cost.
Drawings
FIG. 1 is a schematic perspective view of an intake mass flow measuring device according to the present invention;
FIG. 2 is a schematic cross-sectional view of an intake mass flow measurement apparatus of the present invention;
FIG. 3 is a schematic perspective view of an intake mass flow measuring device according to the present invention;
the device comprises a filter screen 1, an end face guide plate 2, a horn nozzle 3, an AES standard shape, a temperature sensor 4, a pressure stabilizing section 5, a static pressure hole 6 and a ring pipeline 7.
Detailed Description
The embodiments of the present invention are described below with reference to specific embodiments, and other advantages and effects of the present invention will be easily understood by those skilled in the art from the disclosure of the present specification. The invention is capable of other and different embodiments and of being practiced or of being carried out in various ways, and its several details are capable of modification in various respects, all without departing from the spirit and scope of the present invention. It is to be noted that the features in the following embodiments and examples may be combined with each other without conflict.
It should be noted that, in order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention are clearly and completely described below, and it is obvious that the described embodiments are some embodiments of the present invention, but not all embodiments.
Thus, the following detailed description of the embodiments of the present invention is not intended to limit the scope of the invention as claimed, but is merely representative of selected embodiments of the invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. indicate orientations and positional relationships that are conventionally used in the products of the present invention, and are used merely for convenience in describing the present invention and for simplicity in description, but do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," "third," and the like are used solely to distinguish one from another and are not to be construed as indicating or implying relative importance.
Furthermore, the terms "horizontal", "vertical", "overhang" and the like do not imply that the components are required to be absolutely horizontal or overhang, but may be slightly inclined. For example, "horizontal" merely means that the direction is more horizontal than "vertical" and does not mean that the structure must be perfectly horizontal, but may be slightly inclined.
In the description of the present invention, it should also be noted that, unless otherwise explicitly specified or limited, the terms "disposed," "mounted," "connected," and "connected" are to be construed broadly and may, for example, be fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
In addition, it should be noted that, in the present invention, if the specific structures, connection relationships, position relationships, power source relationships, and the like are not written in particular, the structures, connection relationships, position relationships, power source relationships, and the like related to the present invention can be known by those skilled in the art without creative work on the basis of the prior art.
Example 1:
referring to fig. 1 to 3, the invention discloses an air inlet mass flow measuring device of an aircraft engine. The measuring device at least comprises an end surface guide plate 2, a horn nozzle 3, a pressure stabilizing section 5 and an atmospheric pressure gauge for realizing atmospheric pressure measurement. And, the atmospheric pressure gauge is mercury pressure gauge.
Preferably, the deflector 2 is connected to the outer edge of the bell 3. Used for guiding the end face flowing air flow. The contraction end of the horn mouth 3 is connected with the pressure stabilizing section 5, and the other end of the pressure stabilizing section 5 is connected with an air inlet of the aircraft engine.
Preferably, a plurality of temperature sensors 4 are uniformly arranged on the end surface guide plate 2 in the circumferential direction. The temperature measurement of the intake air flow, i.e. the local atmospheric temperature, is done by the temperature sensor 4.
Specifically, the number of the temperature sensors 4 arranged in the circumferential direction of the end surface baffle 2 is 6. The temperature sensor 4 is a T-shaped temperature sensor. Through the setting of multiple temperature sensors 4, the accuracy of atmospheric temperature measurement can be ensured.
Preferably, the middle end side wall of the pressure stabilizing section 5 is provided with an annular pipeline 7. A plurality of static pressure holes 6 are formed in the circumferential direction of the annular pipeline 7. And a total pressure sensor is arranged in the annular pipeline 7.
Specifically, the annular pipeline 7 is uniformly provided with 6 static pressure holes 6 in the circumferential direction. And the total pressure sensor is a high-precision differential pressure transmitter, is arranged in the annular pipeline and is used for measuring the dynamic pressure of the airflow in the pressure stabilizing section. And the measuring range of the differential pressure transmitter can be selected according to the dynamic pressure range in the measuring section so as to improve the measuring precision.
Preferably, the external shape of the bell mouth 3 is an AES bell mouth standard external shape. The overall scaling may be performed as desired so that the dimension L2 of the horn mouth 3 in the flow direction is the same as the diameter D of the surge section 5, as shown in fig. 2. The size of the horn mouth in the flow direction is the same as the diameter of the horn mouth outlet, which is a horn mouth shape parameter and determines the size of the horn mouth.
Preferably, the diameter D of the stabilizer section 5 is the same as the diameter of the aircraft engine air intake. And the length L1 of the pressure stabilizing section 5 is 1.2-1.5 times of the diameter D. By setting the length L1 and the diameter D of the pressure stabilizing section 5, the airflow flowing loss is reduced, and the airflow flowing stability is improved. Thereby the measurement accuracy of this measuring device has been guaranteed.
Preferably, the air inlet end of the trumpet nozzle 3 is also provided with a filter screen 1. The diameter of the filter screen 1 is larger than the outer diameter of the air inlet end of the horn mouth 3. Namely, the air inlet end of the horn mouth 3 is integrally covered by the filter screen 1, so as to prevent mosquitoes from blocking the static pressure hole.
Example 2:
based on the intake mass flow measuring device disclosed in embodiment 1, the invention also discloses a measuring method of the intake mass flow of the aircraft engine.
The method for measuring the air inlet mass flow of the aircraft engine comprises the following steps:
wherein the content of the first and second substances,
ρ is the air density of the pressure stabilizing section 5, v is the airflow velocity in the pressure stabilizing section 5, and a is the flow area in the pressure stabilizing section 5 for mass flow.
Wherein the air density P in the pressure stabilizing section 5 is P0/RT。P0Atmospheric pressure measured by an atmospheric pressure gauge. R is a constant value. T is the intake air temperature. The intake air temperature is measured by the temperature sensor 4.
Flow velocity in the surge section
q is dynamic pressure. The dynamic pressure q is measured by a total pressure sensor arranged in the ring line 7.
The measuring device and the corresponding measuring method disclosed by the invention can realize the quick and high-precision measurement of the mass flow of the inlet air of the engine on the premise of not influencing the working state of the engine, and have the advantages of simple method and low cost.
The foregoing basic embodiments of the invention and their various further alternatives can be freely combined to form multiple embodiments, all of which are contemplated and claimed herein. In the scheme of the invention, each selection example can be combined with any other basic example and selection example at will. Numerous combinations will be known to those skilled in the art.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents and improvements made within the spirit and principle of the present invention are intended to be included within the scope of the present invention.
Claims (10)
1. An air inlet mass flow measuring device of an aircraft engine is characterized in that the measuring device at least comprises an end surface guide plate (2), a horn nozzle (3), a pressure stabilizing section (5) and an atmospheric pressure gauge for realizing atmospheric pressure measurement,
the guide plate (2) is connected with the outer edge of the horn nozzle (3), the contraction end of the horn nozzle (3) is connected with the pressure stabilizing section (5), and the other end of the pressure stabilizing section (5) is connected with an air inlet of an aircraft engine;
a plurality of temperature sensors (4) are uniformly arranged in the circumferential direction of the end face guide plate (2);
the middle end side wall of the pressure stabilizing section (5) is provided with an annular pipeline (7), a plurality of static pressure holes (6) are formed in the circumferential direction of the annular pipeline (7), and a total pressure sensor is arranged in the annular pipeline (7).
2. An aircraft engine intake mass flow measuring device according to claim 1, characterised in that the external shape of the horn mouth (3) is an AES horn mouth standard external shape,
and the dimension L2 of the horn mouth (3) in the flow direction is the same as the diameter D of the pressure stabilizing section (5).
3. An aircraft engine intake mass flow measuring device according to claim 1, characterised in that the diameter D of the surge section (5) is the same as the diameter of the aircraft engine intake;
and the length L1 of the pressure stabilizing section (5) is 1.2-1.5 times of the diameter D.
4. An aircraft engine intake mass flow measuring device according to claim 1, characterised in that the air inlet end of the horn nozzle (3) is further provided with a filter screen (1).
5. An aircraft engine intake mass flow measuring device according to claim 4, characterised in that the diameter of the filter screen (1) is greater than the outer diameter of the intake end of the horn nozzle (3).
6. The aircraft engine intake mass flow measurement device according to claim 1, wherein there are 6 temperature sensors (4) disposed in the circumferential direction of the end baffle (2); the temperature sensor (4) is a T-shaped temperature sensor.
7. The aircraft engine intake mass flow measuring device according to claim 1, characterized in that 6 static orifices (6) are provided in the circumferential direction of the annular duct (7).
8. The aircraft engine intake mass flow measurement device of claim 1, wherein the total pressure sensor is a differential pressure transmitter for measuring the dynamic pressure of the airflow in the surge section.
9. An aircraft engine intake mass flow measurement apparatus according to claim 1, wherein said atmospheric pressure gauge is a mercury pressure gauge.
10. A method for measuring the air inlet mass flow of an aero-engine is characterized by comprising the following steps:
wherein the content of the first and second substances,
rho is the air density of the pressure stabilizing section (5), v is the airflow flowing speed in the pressure stabilizing section (5), and A is the flow area in the pressure stabilizing section (5) for mass flow;
wherein the air density rho ═ P in the pressure stabilization section (5)0/RT，P0Atmospheric pressure, R is a constant value, and T is the inlet air temperature;
and, the flow velocity in the surge section
q is dynamic pressure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010907928.3A CN112197826A (en) | 2020-09-02 | 2020-09-02 | Air inlet mass flow measuring device and measuring method for aircraft engine |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010907928.3A CN112197826A (en) | 2020-09-02 | 2020-09-02 | Air inlet mass flow measuring device and measuring method for aircraft engine |
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| Publication Number | Publication Date |
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| CN112197826A true CN112197826A (en) | 2021-01-08 |
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| CN202010907928.3A Pending CN112197826A (en) | 2020-09-02 | 2020-09-02 | Air inlet mass flow measuring device and measuring method for aircraft engine |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113859577A (en) * | 2021-10-13 | 2021-12-31 | 西北工业大学 | Mobile test bed air inlet channel adaptive to complex outfield environment and design method thereof |
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| CN1595071A (en) * | 2004-06-30 | 2005-03-16 | 上海理工大学 | Detachable combined dynamic pressure for flow and pressure measurement |
| CN102297031A (en) * | 2010-06-28 | 2011-12-28 | 通用汽车环球科技运作有限责任公司 | System and method for measuring engine airflow |
| CN103033334A (en) * | 2012-12-19 | 2013-04-10 | 中国航空工业集团公司沈阳空气动力研究所 | Testing device of flow measurement and control used in aerospace |
| US20170254249A1 (en) * | 2016-03-02 | 2017-09-07 | Watlow Electric Manufacturing Company | Susceptor for use in a fluid flow system |
| CN107270979A (en) * | 2017-05-18 | 2017-10-20 | 东方电气集团东方汽轮机有限公司 | A kind of aerodynamic testing air-flow measurement device |
| CN111024402A (en) * | 2019-12-13 | 2020-04-17 | 湖南汉能科技有限公司 | Aeroengine test bench installing system |
| CN111044296A (en) * | 2019-12-13 | 2020-04-21 | 湖南汉能科技有限公司 | Comprehensive test bed and test method for aero-engine parts |
-
2020
- 2020-09-02 CN CN202010907928.3A patent/CN112197826A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1595071A (en) * | 2004-06-30 | 2005-03-16 | 上海理工大学 | Detachable combined dynamic pressure for flow and pressure measurement |
| CN102297031A (en) * | 2010-06-28 | 2011-12-28 | 通用汽车环球科技运作有限责任公司 | System and method for measuring engine airflow |
| CN103033334A (en) * | 2012-12-19 | 2013-04-10 | 中国航空工业集团公司沈阳空气动力研究所 | Testing device of flow measurement and control used in aerospace |
| US20170254249A1 (en) * | 2016-03-02 | 2017-09-07 | Watlow Electric Manufacturing Company | Susceptor for use in a fluid flow system |
| CN107270979A (en) * | 2017-05-18 | 2017-10-20 | 东方电气集团东方汽轮机有限公司 | A kind of aerodynamic testing air-flow measurement device |
| CN111024402A (en) * | 2019-12-13 | 2020-04-17 | 湖南汉能科技有限公司 | Aeroengine test bench installing system |
| CN111044296A (en) * | 2019-12-13 | 2020-04-21 | 湖南汉能科技有限公司 | Comprehensive test bed and test method for aero-engine parts |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113859577A (en) * | 2021-10-13 | 2021-12-31 | 西北工业大学 | Mobile test bed air inlet channel adaptive to complex outfield environment and design method thereof |
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