阅读说明：本技术 一种飞机用座舱限流和流量测试组合装置 (Cabin current-limiting and flow testing combined device for airplane ) 是由 张书晔 孙宇 傅恽涵 张萌 张学永 于 2019-11-27 设计创作，主要内容包括：本申请属于飞机座舱空气调节技术领域,特别涉及一种飞机用座舱限流和流量测试组合装置。包括：文氏管(1)、压力传感器以及机上测试系统。所述文氏管(1)安装在飞机座舱供气管路中,所述文氏管(1)包括依次连接的入口圆筒段、圆锥收缩段、圆筒喉部以及圆锥扩散段；压力传感器包括两个,一个所述压力传感器设置在所述文氏管(1)的入口圆筒段,另一个所述压力传感器设置在所述文氏管(1)的圆筒喉部；所述机上测试系统与两个所述压力传感器电连接,用于获取两个所述压力传感器的测量值,并根据所述测量值解算出流量值。本申请具有限流以及流量自检测功能,有利于提高精准定位故障能力,降低维护、保障难度,提升飞机的维护性和保障性。(The application belongs to the technical field of air conditioning of aircraft cabins, and particularly relates to a cabin flow limiting and flow testing combined device for an aircraft. The method comprises the following steps: venturi (1), pressure sensor and on-board test system. The venturi (1) is installed in an air supply pipeline of an airplane cabin, and the venturi (1) comprises an inlet cylindrical section, a conical contraction section, a cylindrical throat and a conical diffusion section which are sequentially connected; the pressure sensor comprises two pressure sensors, one pressure sensor is arranged at the inlet cylindrical section of the venturi (1), and the other pressure sensor is arranged at the cylindrical throat part of the venturi (1); the onboard test system is electrically connected with the two pressure sensors and is used for obtaining the measurement values of the two pressure sensors and calculating the flow value according to the measurement values. This application has current-limiting and flow self test function, is favorable to improving accurate positioning fault ability, reduces and maintains, ensures the degree of difficulty, promotes the maintainability and the supportability of aircraft.)

1. A cockpit flow limiting and flow testing combination for an aircraft, comprising:

the air supply system comprises a venturi (1), wherein the venturi (1) is installed in an air supply pipeline of an airplane cabin, and the venturi (1) comprises an inlet cylinder section, a conical contraction section, a cylinder throat and a conical diffusion section which are sequentially connected;

the pressure sensor comprises two pressure sensors, one pressure sensor is arranged at the inlet cylindrical section of the venturi (1), and the other pressure sensor is arranged at the cylindrical throat part of the venturi (1);

and the onboard test system is electrically connected with the two pressure sensors and is used for acquiring the measured values of the two pressure sensors and calculating the flow value according to the measured values.

2. The aircraft cabin flow limiting and flow testing combination device according to claim 1, characterized in that an annular first testing part is arranged on the outer wall of the inlet cylindrical section of the venturi tube (1), a first testing cavity is formed in the first testing part, the first testing cavity is communicated with the inside of the inlet cylindrical section through a first through hole formed in the wall of the inlet cylindrical section, a first pipe joint (2) is installed on the first testing part, and the first pipe joint (2) is connected with one of the pressure sensors.

3. The aircraft cabin flow-limiting and flow-testing combination device according to claim 2, wherein the first through holes are uniformly opened in the circumferential direction at four sides of the wall of the inlet cylindrical section.

4. The aircraft cabin flow limiting and flow testing combination device according to claim 2, characterized in that an annular second testing part is arranged on the outer wall of the cylindrical throat part of the venturi tube (1), a second testing cavity is formed in the second testing part, the second testing cavity is communicated with the inside of the cylindrical throat part through a second through hole formed in the tube wall, a second tube joint (3) is mounted on the second testing part, and the second tube joint (3) is connected with another pressure sensor.

5. The aircraft cabin flow-limiting and flow-testing combined device according to claim 4, wherein the number of the second through holes is four along the circumferential direction on the pipe wall of the cylindrical throat part.

6. The combined cockpit current limiting and flow testing device of claim 1, wherein said onboard testing system is further configured to send said flow value to a flight data logging system via a bus.

7. The cockpit flow restriction and flow test combination according to claim 1, wherein the solving of the flow value by the onboard test system from the measured value is specifically:

calculating the difference value of the measured values of the two pressure sensors to obtain a pressure difference delta p;

calculating the flow rate value q according to the following formula_m：

Where C is the outflow coefficient, β is the diameter ratio D/D, D is the downstream pipe diameter, D is the upstream pipe diameter, ε is the expansion coefficient, ρ₁Is the upstream fluid density.

Technical Field

The application belongs to the technical field of air conditioning of aircraft cabins, and particularly relates to a cabin flow limiting and flow testing combined device for an aircraft.

Background

The air conditioning of the cabin is an important function of an aircraft system, and due to the fact that the related link factors are more, under the condition of no information, great manpower and material resource inspection, test and analysis can be spent when failure occurs and troubleshooting is carried out, and the air conditioning performance of the cabin is directly influenced by the air supply flow state of the cabin.

The cabin air conditioning system of the existing airplane is generally provided with a venturi tube flow limiting device in a cabin air supply pipeline to limit the maximum flow of a cabin and prevent the excessive flow of the cabin from causing the pressure overshoot of the cabin to cause structural damage or injury to a pilot. The device only plays the effect of current-limiting, can't give the specific information of cabin air feed flow, increases the aircraft and maintains, ensures the degree of difficulty.

Accordingly, a technical solution is desired to overcome or at least alleviate at least one of the above-mentioned drawbacks of the prior art.

Disclosure of Invention

The application aims to provide a cockpit flow limiting and flow testing combined device for an airplane, so as to solve at least one problem existing in the prior art.

The technical scheme of the application is as follows:

a cockpit flow limiting and flow testing combination for an aircraft, comprising:

the venturi is installed in an air supply pipeline of the aircraft cabin and comprises an inlet cylindrical section, a conical contraction section, a cylindrical throat and a conical diffusion section which are sequentially connected;

the pressure sensor comprises two pressure sensors, one pressure sensor is arranged at the inlet cylindrical section of the venturi, and the other pressure sensor is arranged at the cylindrical throat part of the venturi;

and the onboard test system is electrically connected with the two pressure sensors and is used for acquiring the measured values of the two pressure sensors and calculating the flow value according to the measured values.

Optionally, an annular first testing part is arranged on the outer wall of the inlet cylindrical section of the venturi tube, a first testing cavity is formed in the first testing part, the first testing cavity is communicated with the inside of the inlet cylindrical section through a first through hole formed in the tube wall, a first tube joint is installed on the first testing part, and the first tube joint is connected with one pressure sensor.

Optionally, the first through holes are uniformly formed in the circumferential direction on the pipe wall of the inlet cylindrical section.

Optionally, an annular second testing part is arranged on the outer wall of the cylinder throat of the venturi, a second testing cavity is formed in the second testing part, the second testing cavity is communicated with the inside of the cylinder throat through a second through hole formed in the tube wall, a second tube joint is mounted on the second testing part, and the second tube joint is connected with the other pressure sensor.

Optionally, the second through holes are uniformly formed in the circumferential direction on the tube wall of the cylindrical throat portion.

Optionally, the onboard test system is further configured to send the flow value to a flight data recording system via a bus.

Optionally, the calculating, by the onboard test system according to the measurement value, a flow value specifically includes:

calculating the difference value of the measured values of the two pressure sensors to obtain a pressure difference delta p;

calculating the flow rate value q according to the following formula_m：

Where C is the outflow coefficient, β is the diameter ratio D/D, D is the downstream pipe diameter, D is the upstream pipe diameter, ε is the expansion coefficient, ρ₁Is the upstream fluid density.

The invention has at least the following beneficial technical effects:

the utility model provides a passenger cabin current-limiting and flow test composite set for aircraft, integrated design through passenger cabin current-limiting and flow test, increase passenger cabin air feed flow self-detection function on the basis of passenger cabin air supply line current-limiting effect, original function has been guaranteed promptly, can appear passenger cabin temperature regulation abnormity again in the aircraft use, provide accurate state information when trouble shooting such as passenger cabin pressure can't maintain, be favorable to improving accurate location fault ability, the maintenance that causes because of the data disappearance has been reduced, the guarantee degree of difficulty, the maintainability and the guarantee nature of promotion aircraft.

Drawings

FIG. 1 is a schematic view of a combined current limiting and flow testing device for an aircraft cockpit according to one embodiment of the present application;

fig. 2 is a graph of the resistance characteristics of different venturis.

Wherein:

1-a venturi; 2-a first pipe joint; 3-second pipe joint.

Detailed Description

In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are a subset of the embodiments in the present application and not all embodiments in the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application and should not be construed as limiting the present application. 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 application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.

In the description of the present application, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present application and for simplifying the description, and do not indicate or imply that the referenced device or element must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore should not be construed as limiting the scope of the present application.

The present application is described in further detail below with reference to fig. 1-2.

The application provides a passenger cabin current-limiting and flow test composite set for aircraft includes: venturi 1, pressure sensor and on-board test system.

Specifically, the venturi 1 is installed in an air supply pipeline of an airplane cabin, and the venturi 1 comprises an inlet cylindrical section, a conical contraction section, a cylindrical throat and a conical diffusion section which are sequentially connected; the pressure sensors comprise two pressure sensors, one pressure sensor is arranged at the inlet cylindrical section of the venturi 1, and the other pressure sensor is arranged at the cylindrical throat part of the venturi 1; the onboard test system is electrically connected with the two pressure sensors and is used for acquiring the measured values of the two pressure sensors and calculating the flow value according to the measured values.

The utility model provides a passenger cabin current-limiting and flow test composite set for aircraft, the main part adopts the venturi structure, adds the pressure detection structure at entry cylinder section and cylinder throat to realize that work detects the real-time velocity of flow function of gas through the product in the state. The inlet cylindrical section is designed in an inlet form as shown in figure 1 according to actual installation requirements, a pressure taking port and a testing part of the pressure detection device are designed as shown in figure 1 according to assembly requirements, the conical diffusion section is of a classical conical structure, and a cut-off type Venturi nozzle structure with a suggested value of 7-12 degrees is adopted according to flight design manual and product size requirements and parameters 2 theta of the conical diffusion section. As shown in fig. 2, under the same differential pressure Δ p, the smaller the size of the venturi throat, the stronger the flow restriction; within a certain range, the flow rate of the fluid is continuously enhanced along with the increase of the differential pressure between the upstream side and the downstream side of the throat part of the venturi tube, so that the flow rate value of the fluid is continuously improved, when the differential pressure delta p exceeds a certain value, the flow rate of the fluid is not increased along with the increase of the differential pressure, therefore, the flow rate value of the fluid tends to be stable, and the flow limiting effect of the venturi tube is exerted to the maximum state at the moment.

In an embodiment of the application, the pressure taking port of the pressure detection device is designed in a manner that an annular first testing part is arranged on the outer wall of the inlet cylindrical section of the venturi 1, a first testing cavity is formed in the first testing part, the first testing cavity is communicated with the inside of the inlet cylindrical section through a first through hole formed in the pipe wall, a first pipe joint 2 is installed on the first testing part, and the first pipe joint 2 is connected with a pressure sensor. Four first through holes are uniformly formed in the circumferential direction of the pipe wall of the inlet cylindrical section. An annular second testing part is arranged on the outer wall of the cylinder throat part of the venturi tube 1, a second testing cavity is formed in the second testing part, the second testing cavity is communicated with the inside of the cylinder throat part through a second through hole formed in the tube wall, a second tube joint 3 is installed on the second testing part, and the second tube joint 3 is connected with another pressure sensor. The second through holes are uniformly formed in the circumferential direction on the tube wall of the throat part of the cylinder.

According to the cabin flow limiting and flow testing combined device for the airplane, fluid filled in a pipeline flows through the venturi 1, the flow stream forms local contraction at the venturi 1, so that the flow speed is increased, the static pressure is reduced, and a static pressure difference is generated between the upstream side and the throat or the downstream side of the venturi 1. The larger the flow velocity of the fluid is, the larger the differential pressure generated before and after the venturi 1 is, so that the flow rate of the fluid passing through the venturi 1 can be measured by measuring the differential pressure, and the measuring method is based on the law of conservation of energy and the equation of continuity of flow. The two pressure sensors respectively measure the absolute static pressure of the fluid at the upstream side and the downstream side of the venturi 1 to further obtain a static pressure difference value delta p, the signals of the pressure difference sensors are collected and analyzed in real time through an on-board test system, and a flow value q is determined according to the actual measured value of the pressure difference, the characteristics of the flowing fluid, the temperature state of the using environment of the device and other information_mThe relationship with the differential pressure Δ p can be solved by the following equation:

wherein C is the outflow coefficient, β is the diameter ratio D/D, D is the downstream pipeline straightDiameter, D the upstream pipe diameter, ε the coefficient of expansion, ρ₁Is the upstream fluid density.

In one embodiment of the application, the resolved data is sent by the onboard test system to the flight data recording system for recording and storage through a high-speed data bus network.

The cockpit flow limiting and flow testing combination device for the airplane increases the function of fluid flow self-detection on the basis of maintaining the flow limiting effect of a cockpit pipeline, fundamentally solves the problem that a flight data recording system has no data record on the air flow of the cockpit pipeline, provides necessary data support for aircraft maintenance and guarantee work in the future, reduces the difficulty in troubleshooting faults such as abnormal cockpit temperature regulation and incapability of maintaining a cockpit pressure system, realizes integrated and comprehensive design, has the characteristics of miniaturization, light weight and intellectualization, is suitable for various fluid flow fields including design of an airplane environment control system, and has great military and civil application values.

The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.