Fuel oil pipeline for measuring fuel oil flow of engine for aircraft flight test

Abstract

The fuel oil pipeline for measuring the fuel oil flow of the engine for the aircraft flight test comprises a pipeline inlet; the pipeline outlet is positioned at the downstream of the pipeline inlet along the pipeline extending direction; the bending part divides the fuel oil pipeline into a first pipeline part and a second pipeline part on the upstream and the downstream in the pipeline extending direction; the first flow meter is arranged on the first pipeline part so as to sense the flow of fuel oil flowing through the first pipeline part; the first flow meter is arranged on the first pipeline part, the second flow meter is arranged on the second pipeline part and used for sensing the flow of fuel oil flowing through the second pipeline part, and the first flow meter and the second flow meter have different flow sensing characteristics. A temperature and / or pressure sensor used for correcting the fuel oil density and viscosity can be selected, so that the fuel oil flow is corrected. According to the fuel oil pipeline disclosed by the utility model, a high-precision fuel oil flow measurement value of the engine can be obtained in an irregular narrow annular space under the condition of a large flow range from an engine starting state to a maximum power state, so that high-precision and wide-range fuel oil flow measurement is realized.

Description

Technical Field

[0001] This utility model relates to a fuel pipeline for measuring engine fuel flow in aircraft flight tests, used to measure fuel flow under various operating conditions such as engine start-up and idle speed during flight tests. Background Technology

[0002] In the development and airworthiness certification of various aircraft, including civil transport aircraft, precise measurement of engine fuel flow is required for aircraft carbon emission measurement, aircraft performance, aircraft fuel system, and power plant system development and airworthiness certification flight tests. Typically, the measurement accuracy of fuel mass flow rate needs to reach 0.25%.

[0003] Generally speaking, aero engines operate within a wide flight envelope (-2000–45000 ft, 0–0.89 Mach number). During flight testing, the engine may be in various operating conditions, such as shutdown (windmill state), start-up, idle, acceleration / deceleration, and maximum power. The range of fuel flow variation is large under different operating conditions.

[0004] When selecting a flow meter for a specific application, the applicable calibration area should be considered. Typically, rotor-type fuel flow meters are only suitable for measuring the flow range on the side where the hinge curves coincide at the breakaway point. Therefore, a single fuel flow meter is often not applicable for measuring fuel flow across the entire engine operating range.

[0005] During the operation of an aircraft engine, fuel and engine oil exchange heat. The fuel temperature varies over a wide range (e.g., -40℃ to 100℃), and the density and viscosity of the fuel are significantly affected by temperature.

[0006] The fuel pump pressure changes with engine speed. To accurately measure fuel flow, the physical properties of fuel, such as density and viscosity, need to be corrected for temperature and pressure. When measuring fuel flow, fuel temperature and pressure parameters need to be collected simultaneously.

[0007] The internal structure of an aircraft engine nacelle is complex and the installation space is limited. The fuel flow meter needs to be installed on a straight section of the fuel line, and the length of the straight section must be no less than 10 times the diameter of the line, making it difficult to install inside the engine nacelle. Utility Model Content

[0008] In view of the above-mentioned defects in the existing technology, in order to solve the above problems and obtain high-precision engine fuel flow measurement values ​​under different operating conditions, this utility model designs a hairpin-type pipeline structure for high-precision measurement of fuel flow in aviation turbofan engines.

[0009] Specifically, this utility model provides a fuel pipeline for measuring engine fuel flow rate in aircraft flight tests, comprising:

[0010] Pipe inlet;

[0011] The pipe outlet is located downstream of the pipe inlet along the direction of pipe extension;

[0012] At least one bend that divides the fuel line into an upstream first section and a downstream second section in the direction of line extension, wherein the direction of line extension changes at the bend.

[0013] A first flow meter, disposed on the first pipeline section, is used to sense the fuel flow rate through the first pipeline section; and

[0014] A second flow meter is installed on the second pipeline section to sense the fuel flow rate through the second pipeline section.

[0015] The first flow meter and the second flow meter have different flow sensing characteristics.

[0016] According to a preferred but non-limiting embodiment of the fuel pipeline for measuring engine fuel flow rate in aircraft flight tests of the present invention, at least a portion of the first pipeline section is a straight pipe segment extending along a first pipeline direction, at least a portion of the second pipeline section is a straight pipe segment extending along a second pipeline direction, and the angle between the first pipeline direction and the second pipeline direction is less than 45°.

[0017] According to a preferred but non-limiting embodiment of the fuel pipeline for measuring engine fuel flow rate in aircraft flight testing according to the present invention, the first pipeline direction and the second pipeline direction are parallel to each other.

[0018] According to a preferred but non-limiting embodiment of the fuel line for measuring engine fuel flow in aircraft flight tests of this utility model, the first flow meter and the second flow meter have different high-precision flow sensing ranges with an accuracy of 0.25%.

[0019] According to a preferred but non-limiting embodiment of the fuel line for measuring engine fuel flow in aircraft flight tests of the present invention, the high-precision flow sensing range of the first flow meter and the high-precision flow sensing range of the second flow meter at least partially overlap.

[0020] According to a preferred but non-limiting embodiment of the fuel pipeline for measuring engine fuel flow in aircraft flight tests of this utility model, the high-precision flow sensing range of the first flow meter is 8000pph-4000pph (pph is pounds per hour, a unit of flow rate), and the high-precision flow sensing range of the second flow meter is 5000pph-1000pph.

[0021] A preferred, but not limiting, embodiment of the fuel line for measuring engine fuel flow in an aircraft flight test according to the present invention includes only one of the aforementioned bends.

[0022] According to a preferred but non-limiting embodiment of the fuel pipeline for measuring engine fuel flow in aircraft flight tests of this utility model, the fuel pipeline is provided with a temperature sensor and a pressure sensor upstream and downstream of the bend, respectively.

[0023] According to a preferred but non-limiting embodiment of the fuel pipeline for measuring engine fuel flow rate in aircraft flight tests of this utility model, a temperature sensor and a pressure sensor upstream of the bend are arranged upstream of the first flow meter, and a temperature sensor and a pressure sensor downstream of the bend are arranged downstream of the second flow meter, so as to sense the temperature and pressure of the fuel passing through the first flow meter and the second flow meter respectively.

[0024] Measuring the temperature and pressure of fuel can be used to correct for fuel density and viscosity, and thus fuel flow rate, thereby helping to achieve high-precision measurements.

[0025] According to a preferred but non-limiting embodiment of the fuel line for measuring engine fuel flow rate in aircraft flight testing according to the present invention, the fuel line includes a bend between various straight sections to change the extension direction of the line between the various straight sections.

[0026] In summary, this utility model effectively designs a hairpin-type fuel pipeline structure by incorporating bends in the pipeline. This satisfies the requirement for a straight section of pipeline for fuel flow measurement within the limited space of the engine nacelle. It also enables the series installation and fixation of upstream and downstream pressure sensors, temperature sensors, and fuel flow meters with different flow ranges in the fuel pipeline. This allows for high-precision (e.g., within 0.25%) and large-range (e.g., 8000pph-1000pph) fuel flow measurement in irregular and narrow annular spaces. Attached Figure Description

[0027] This document includes accompanying drawings to provide a further understanding of various embodiments. The drawings are incorporated in and form part of this specification.

[0028] The accompanying drawings illustrate various embodiments described herein and, together with the textual description, serve to explain the principles and operation of the claimed subject matter.

[0029] With reference to the above objectives, the technical features of this utility model are clearly described below, and its advantages are apparent from the following detailed description with reference to the accompanying drawings, which illustrate preferred embodiments of the utility model by way of example, without limiting the scope of the utility model.

[0030] In the attached image:

[0031] Figure 1 The present invention illustrates the fuel pipeline for measuring engine fuel flow rate in aircraft flight tests.

[0032] List of reference numerals

[0033] 100 Fuel Line

[0034] 110 Pipe Inlet

[0035] 120 Pipeline Outlet

[0036] 130 bend

[0037] 140 First Pipeline Section

[0038] 150 Second Pipeline Section

[0039] 160 First Flow Meter

[0040] 170 Second Flow Meter

[0041] 180 temperature sensor

[0042] 190 Pressure Sensor Detailed Implementation

[0043] Embodiments of the present invention will now be described in detail, examples of which are shown in the accompanying drawings and described below.

[0044] Although the present invention will be described in conjunction with exemplary embodiments, it should be understood that this specification is not intended to limit the present invention to the embodiments illustrated.

[0045] Conversely, this invention is intended to cover not only these exemplary embodiments, but also various alternative forms, modifications, equivalent forms and other embodiments that may be included within the spirit and scope of this invention.

[0046] To facilitate explanation and precise definition of the technical solution of this utility model, the terms "upper", "lower", "inner" and "outer" are used to describe these features with reference to the positions of the features in the exemplary embodiments shown in the accompanying drawings.

[0047] The fuel line 100 for measuring engine fuel flow in aircraft flight tests according to this invention will be described in detail below with reference to the accompanying drawings.

[0048] Those skilled in the art will understand that the aircraft test flights referred to herein include, but are not limited to, engine test flights, aircraft performance test flights, and fuel system test flights for large civil or non-civilian passenger aircraft and / or other purpose aircraft.

[0049] like Figure 1 As shown, the fuel line 100 includes a line inlet 110, a line outlet 120 located downstream of the line inlet 110 along the line extension direction, at least one bend 130, a first flow meter 160, and a second flow meter 170.

[0050] Among them, the bend 130 bends the fuel line 100 in the direction of line extension ( Figure 1 (Indicated by arrows) It is divided into an upstream first pipe section 140 and a downstream second pipe section 150. At the bend 130, the pipe's direction of extension changes. It should be noted that... Figure 1 The specific bending form of the bending portion 130 is only for illustration. Those skilled in the art can select various specific shapes of the bending portion 130 according to actual needs. Preferably, it is to allow fuel to flow smoothly through the bending portion 130.

[0051] It is understood that the first pipeline section 140 and the second pipeline section 150 are separated by a certain distance. Those skilled in the art can design the distance between them appropriately according to actual installation requirements and space conditions, which will not be elaborated here.

[0052] It should also be pointed out that, although Figure 1 Only one bend 130 is shown in the diagram, but according to the basic concept of this utility model, the fuel line 100 may also include multiple bends 130. Of course, depending on actual needs, the fuel line 100 may include only one bend 130. The bend 130 makes the fuel line 100 of this utility model form a "hairpin" shape.

[0053] A first flow meter 160 is disposed on a first pipeline section 140 to sense the fuel flow rate through the first pipeline section 140.

[0054] A second flow meter 170 is installed on the second pipeline section 150 to sense the fuel flow rate through the second pipeline section 150.

[0055] In the preferred embodiment ( Figure 1 (Not shown in the image), the fuel line 100 may also include a fan housing mounting bracket to enable the structure of the fuel line 100 of this utility model to be installed on the engine fan housing in order to meet the test requirements.

[0056] It is understandable that the first flow meter 160 and the second flow meter 170, located upstream and downstream of the bend 130 respectively, are connected in series on the fuel line 100.

[0057] According to the concept of this utility model, the first flow meter 160 and the second flow meter 170 have different flow sensing characteristics. Specifically, according to the preferred concept of this utility model, the maximum value of the high-precision flow range sensed by the first flow meter is greater than the maximum value of the high-precision flow range sensed by the second flow meter, and the minimum value of the high-precision flow range sensed by the first flow meter is less than the maximum value of the high-precision flow range sensed by the second flow meter, but greater than the minimum value of the high-precision flow range sensed by the second flow meter, thereby achieving high-precision fuel flow sensing over a wide range. Preferably, for example, the high-precision flow sensing ranges of 0.25% or better achieved by the first flow meter 160 and the second flow meter 170 are different. Specifically, the high-precision flow sensing ranges of the first flow meter 160 and the second flow meter 170 can at least partially overlap. By way of example only, according to a preferred embodiment, the high-precision flow sensing range of the first flow meter 160 is 8000pph-4000pph or 8000pph-3000pph, and the high-precision flow sensing range of the second flow meter 170 is 5000pph-1000pph or 6000pph-1000pph. As another example, according to a preferred embodiment, the first flow meter 160 and the second flow meter 170 may have different flow ranges. More preferably, the flow range of the first flow meter 160 may be larger than the flow range of the second flow meter 170.

[0058] It should be noted that, provided that the above basic requirements and optional preferred embodiments are met, those skilled in the art can select a suitable flow meter model according to actual needs to meet the installation requirements on the fuel line 100 and the desired flow sensing requirements, which will not be elaborated here.

[0059] according to Figure 1 In the preferred embodiment of the present invention shown, a portion of the first conduit portion 140 adjacent to the bend 130 may be a portion extending from the bend 130 along the first conduit direction. Figure 1 A straight pipe section extending from the upper right to the lower left, and a portion of the second pipe section adjacent to the bend 130 may be from the bend 130 along the direction of the second pipe ( Figure 1A straight pipe section extending from the upper left to the lower right. The angle between the first and second pipe directions can be less than 45°, for example less than 30°, less than 15°, or approximately 10°. Figure 1 In embodiments not shown, preferably, the first pipeline direction and the second pipeline direction are parallel or substantially parallel to each other, and the included angle between them can be considered to be 0° or approximately 0°.

[0060] The fuel line 100 is preferably equipped with a temperature sensor 180 upstream of the bend 130 and a pressure sensor 190 downstream of the bend 130. In other words, according to this preferred embodiment, such as... Figure 1 As shown, at least two temperature sensors 180 and at least two pressure sensors 190 may be installed on the fuel line 100.

[0061] More specifically, as in Figure 1 As schematically shown, a temperature sensor 180 and a pressure sensor 190 upstream of the bend 130 are arranged upstream of the first flow meter 160, and a temperature sensor 180 and a pressure sensor 190 downstream of the bend 130 are arranged downstream of the second flow meter 170, to respectively sense the temperature and pressure of the fuel passing through the first flow meter 160 and the second flow meter 170. It is readily understood that in this arrangement, the temperature sensor 180 and the pressure sensor 190 upstream of the bend 130 measure the temperature and pressure of the fuel about to flow into the first flow meter 160, and the temperature sensor 180 and the pressure sensor 190 downstream of the bend 130 measure the temperature and pressure of the fuel just flowing out of the second flow meter 170. It can be considered that this arrangement of temperature sensors 180 and pressure sensors 190 measures the temperature and pressure of the fuel passing through the first flow meter 160 and the second flow meter 170.

[0062] It should be noted that the specific models of the temperature sensor 180 and pressure sensor 190 can be selected according to actual needs. For example, those skilled in the art can select a temperature and pressure sensor that can simultaneously measure fuel temperature and pressure. This is within the scope that those skilled in the art can achieve according to specific sensing needs, so it will not be elaborated here.

[0063] Furthermore, it should be noted that those skilled in the art can preferably implement the measurement timing control of each flow meter 160, 170 and temperature sensor 180 and pressure sensor 190 through software and hardware according to actual needs.

[0064] For example, the first flow meter 160, temperature sensor 180 and pressure sensor 190 upstream of the bend 130 are made to measure substantially simultaneously, so that the fuel being sensed by the three is substantially the same.

[0065] Similarly, the second flow meter 170, temperature sensor 180 and pressure sensor 190 downstream of the bend 130 can be measured substantially simultaneously, so that the fuel being sensed by the three is substantially the same.

[0066] The sensing timing of the first flow meter 160 and the second flow meter 170 can also be coordinated according to actual needs, so that the fuel sensed by the two and / or their matched temperature sensor 180 and pressure sensor 190 is basically the same.

[0067] Furthermore, the temperature sensor 180 and pressure sensor 190 of the first flow meter 160 and the second flow meter 170, as well as their sensing duration and data processing for the same fuel object, are all designs that can be made by those skilled in the art according to actual needs, and will not be elaborated here.

[0068] Considering the installation and arrangement of fuel lines in actual test environments, the aforementioned fuel line 100 can preferably extend along a generally cylindrical curved surface in the pipeline extension direction. Specifically, the fuel line 100 includes bends between various straight sections to change the pipeline extension direction between the various straight sections. The aforementioned straight sections can be used to mount temperature sensors 180, pressure sensors 190, and / or flow meters 160, 170, etc. The aforementioned bends can include relatively smooth bends or relatively abrupt bends. In other words, in Figure 1 In the embodiment shown, the fuel line 100 extends along a cylindrical surface about a generally vertical axis. In this case, those skilled in the art can obtain the aforementioned straight section required for the experiment through suitable design, which will not be elaborated further here.

[0069] In summary, this invention achieves high-precision fuel flow measurement over a wide range on a single fuel pipeline by using two fuel flow meters with different ranges connected in series upstream and downstream. Furthermore, by installing fuel temperature and fuel pressure sensors upstream and downstream respectively, and by selecting temperature and pressure values ​​closer to the corresponding fuel flow meters, the flow parameters of the two sensing characteristics are corrected, thus solving the problem of the impact of large-scale fluctuations in fuel temperature and pressure on fuel flow measurement under actual operating conditions.

[0070] In actual testing, the structure of the fuel line 100 of the above-mentioned preferred embodiments of this utility model was installed or modified inside the engine compartment.

[0071] For example, during installation or modification, it is preferable to remove a section of the existing fuel line. The fuel inlet 110 connects to the fuel supply line from the engine fuel metering unit (FMU), and the fuel outlet 120 connects to the fuel supply line leading to the engine combustion chamber. Preferably, this structure can be fixed to the engine fan housing using an engine fan housing mounting bracket, and the cables for the two high-precision fuel flow meters 160 and 170, two temperature sensors 180, and two pressure sensors 190 located upstream and downstream of the bend 130 can be connected to a data acquisition unit in the testing equipment.

[0072] The data acquisition device and related circuit layout are all available for purchase on the market or based on existing experience by those skilled in the art, and will not be described in detail here.

[0073] In addition, those skilled in the art can install corresponding mounting brackets on each straight pipe section according to actual needs, and some mounting brackets can fix multiple straight pipe sections at the same time.

[0074] The preferred embodiments of the present invention have been described in detail above, but it should be understood that, if necessary, aspects of the embodiments can be modified to utilize aspects, features, and concepts from various patents, applications, and publications to provide other embodiments.

[0075] Given the detailed description above, various readily conceivable variations can be made to the embodiments described herein.

[0076] Generally speaking, the terminology used in the claims should not be considered as limited to the specific embodiments disclosed in the specification and claims, but should be understood to include all possible embodiments together with the full scope of equivalents enjoyed by the claims.

Claims

1. An engine fuel flow measuring fuel line (100) for aircraft flight test, characterized in that it comprises: a line inlet (110); a line outlet (120) downstream of the line inlet (110) in a line extension direction; at least one bend (130) dividing the fuel line (100) in the line extension direction into a first line section (140) upstream thereof and a second line section (150) downstream thereof, at which the line extension direction changes; a first flow meter (160) arranged on the first line section (140) to sense a fuel flow through the first line section (140); and a second flow meter (170) arranged on the second line section (150) to sense a fuel flow through the second line section (150), wherein the first flow meter (160) and the second flow meter (170) have different flow sensing characteristics.

2. The fuel line (100) according to claim 1, characterized in that at least a portion of the first line section (140) is a straight tube section extending in a first line direction, at least a portion of the second line section is a straight tube section extending in a second line direction, and an angle between the first line direction and the second line direction is less than 45°.

3. The fuel line (100) according to claim 2, characterized in that the first line direction and the second line direction are parallel to each other.

4. The fuel line (100) according to claim 1, characterized in that high-accuracy flow sensing intervals of 0.25% accuracy of the first flow meter (160) and the second flow meter (170) are different.

5. The fuel line (100) according to claim 4, characterized in that the high-accuracy flow sensing interval of the first flow meter (160) and the high-accuracy flow sensing interval of the second flow meter (170) at least partially overlap.

6. The fuel line (100) according to claim 5, characterized in that the high-accuracy flow sensing interval of the first flow meter (160) is 8000 pph - 4000 pph, and the high-accuracy flow sensing interval of the second flow meter (170) is 5000 pph - 1000 pph.

7. The fuel line (100) according to claim 1, characterized in that it comprises only one bend (130).

8. The fuel line (100) according to claim 1, characterized in that the fuel line (100) is provided with a temperature sensor (180) and a pressure sensor (190) upstream and downstream of the bend (130), respectively.

9. The fuel line (100) according to claim 8, characterized in that Temperature sensors (180) and pressure sensors (190) upstream of the bend (130) are arranged upstream of the first flow meter (160) and temperature sensors (180) and pressure sensors (190) downstream of the bend (130) are arranged downstream of the second flow meter (170) to sense the temperature and pressure of the fuel passing through the first flow meter (160) and the second flow meter (170) respectively.

10. The fuel line (100) according to claim 1, characterized in that the fuel line (100) comprises a turn between each straight section to change the direction of the line extension between each straight section.

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