An aircraft engine exhaust temperature warning system

Abstract

This application provides an aircraft engine exhaust temperature warning system, which belongs to the technical field of avionics. Specifically, the processor is used to receive wheel load signals, engine speed, air pressure altitude, atmospheric static temperature, and engine throttle angle signals to determine whether the engine exhaust temperature exceeds the corresponding warning temperature in the current flight environment and flight state. The aircraft's engine exhaust temperature warning thresholds vary in different flight environments and flight states. Through the processing scheme of this application, different engine exhaust temperature warning temperatures are designed according to the aircraft's different flight states and flight environments, thereby improving the accuracy of the warning.

Description

Technical Field

[0001] The present application relates to the field of avionics, and in particular to an aircraft engine exhaust temperature warning system. Background Art

[0002] In the field of avionics, engine exhaust temperature signals are a crucial signal collected by flight parameter collectors and displayed on displays. Real-time display of exhaust temperature alarm status is crucial for pilots to understand the aircraft's engine exhaust temperature and operating status. Previously, exhaust temperature measurement circuits, centered around temperature-sensitive resistors, directly displayed the collected temperature. Because exhaust temperature alarm limits are dependent on parameters such as wheel-load signals, engine speed, and air pressure altitude, warnings based solely on exhaust temperature were inaccurate, misleading pilots and potentially causing flight failures. Summary of the Invention

[0003] In view of this, the present application provides an aircraft engine exhaust temperature alarm system, which solves the problems in the prior art and designs different aircraft engine exhaust temperature alarm temperatures according to different flight states and flight environments to improve the accuracy of the alarm.

[0004] The present application provides an aircraft engine exhaust temperature warning system that adopts the following technical solutions:

[0005] An aircraft engine exhaust temperature warning system includes a processor, a wheel-load signal acquisition unit, an engine speed acquisition unit, a pressure altitude acquisition unit, an atmospheric static temperature acquisition unit, and an engine throttle acquisition unit; the wheel-load signal acquisition unit is used to acquire the aircraft's wheel-load signal; the engine speed acquisition unit is used to acquire the aircraft's engine speed; the pressure altitude acquisition unit is used to acquire the aircraft's pressure altitude; the atmospheric static temperature acquisition unit is used to acquire the atmospheric static temperature; and the engine throttle acquisition unit is used to acquire the aircraft's engine throttle angle.

[0006] The processor is used to receive wheel load signals, engine speed, pressure altitude, atmospheric static temperature, and engine throttle angle signals to determine whether the engine exhaust temperature exceeds the corresponding warning temperature in the current flight environment and flight state. The threshold value of the engine exhaust temperature warning varies in different flight environments and flight states;

[0007] When the aircraft is on the ground:

[0008] When the engine speed is less than or equal to the preset speed ratio, the exhaust temperature warning temperature is the first warning temperature;

[0009] When the engine speed is greater than the preset speed ratio, and the aircraft altitude is greater than or equal to the first preset altitude, the atmospheric static temperature is less than or equal to the first preset temperature, and the engine throttle angle is greater than or lower than the first preset angle, the exhaust temperature warning temperature is the second warning temperature;

[0010] When any one of the following three conditions is not met: the aircraft altitude is greater than or equal to the first preset altitude, the atmospheric static temperature is less than or equal to the first preset temperature, and the engine throttle angle is greater than or lower than the first preset angle: when the atmospheric static temperature is less than the second preset temperature, the exhaust temperature alarm temperature is the third alarm temperature; when the atmospheric static temperature is greater than the third preset temperature, the exhaust temperature alarm temperature is the fourth alarm temperature, wherein the first preset temperature is greater than the second preset temperature and less than the third preset temperature.

[0011] Optionally, the preset speed ratio is 69.5%, the first alarm temperature is 690℃; the first preset altitude is 2000m, the first preset temperature is 16℃, the first preset angle is 84°, the second alarm temperature is 550℃; the second preset temperature is 15℃, the third alarm temperature is 520℃; the third preset temperature is 17℃, and the fourth alarm temperature is 570℃.

[0012] Optionally, when the aircraft is in flight and the flight altitude is less than the first flight altitude:

[0013] When the engine throttle angle is greater than or equal to 0° and less than or equal to the second preset angle, the exhaust temperature warning temperature is the fifth warning temperature;

[0014] When the engine throttle angle is greater than the second preset angle and less than or equal to the first preset angle, the exhaust temperature warning temperature is the sixth warning temperature;

[0015] When the engine throttle angle is greater than the first preset angle, the exhaust temperature warning temperature is the seventh warning temperature.

[0016] Optionally, the second preset angle is 68°, the fifth alarm temperature is 500°C; the sixth alarm temperature is 540°C; and the seventh alarm temperature is 620°C.

[0017] Optionally, when the aircraft is in flight and the flight altitude is greater than or equal to the second flight altitude:

[0018] When the engine throttle angle is greater than or equal to 0° and less than or equal to the second preset angle, the exhaust temperature warning temperature is the eighth warning temperature;

[0019] When the engine throttle angle is greater than the second preset angle and less than or equal to the first preset angle, the exhaust temperature warning temperature is the ninth warning temperature;

[0020] When the engine throttle angle is greater than the first preset angle, the exhaust temperature warning temperature is the tenth warning temperature.

[0021] Optionally, the eighth alarm temperature is 520°C, the ninth alarm temperature is 570°C, and the tenth alarm temperature is 620°C.

[0022] Optionally, the first preset altitude is 6500 meters, the second flight altitude is 6550 meters, and when the aircraft rises from 6500 meters to 6550 meters, the range between 6500-6550 meters is set to less than 6500 meters, and when the aircraft descends from 6550 meters to 6500 meters, the range between 6500-6550 meters is set to greater than or equal to 6550 meters.

[0023] Optionally, for every 1°C increase in the aircraft's flight environment temperature compared to the standard temperature, each exhaust warning temperature increases by 1°C; for every 1°C decrease in the aircraft's flight environment temperature compared to the standard temperature, each exhaust warning temperature decreases by 1°C.

[0024] In summary, this application has the following beneficial technical effects:

[0025] Different air engine exhaust temperature warning temperatures are designed according to different flight conditions and flight environments to improve the accuracy of the alarm. By collecting multiple parameters and making logical judgments, logical alarm states are realized with different colors and icon areas. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the following briefly introduces the drawings required for use in the embodiments. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without any creative work.

[0027] Figure 1 This is the principle block diagram of the aircraft engine exhaust temperature warning system for this application. DETAILED DESCRIPTION

[0028] The embodiments of the present application are described in detail below with reference to the accompanying drawings.

[0029] The following describes the embodiments of the present application through specific examples, and those skilled in the art can easily understand other advantages and effects of the present application from the contents disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. The present application can also be implemented or applied through other different specific embodiments, and the details in this specification can also be modified or changed in various ways based on different viewpoints and applications without departing from the spirit of the present application. It should be noted that, in the absence of conflict, the features in the following embodiments and embodiments can be combined with each other. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without making creative work are within the scope of protection of this application.

[0030] It should be noted that various aspects of the embodiments within the scope of the appended claims are described below. It should be apparent that the aspects described herein can be embodied in a wide variety of forms, and any specific structure and / or function described herein is merely illustrative. Based on this application, it should be understood by those skilled in the art that an aspect described herein can be implemented independently of any other aspect, and two or more of these aspects can be combined in various ways. For example, any number of aspects described herein can be used to implement an apparatus and / or practice a method. In addition, other structures and / or functionalities other than one or more of the aspects described herein can be used to implement this apparatus and / or practice this method.

[0031] It should also be noted that the illustrations provided in the following embodiments are only schematic illustrations of the basic concept of the present application. The illustrations only show components related to the present application and are not drawn according to the number, shape and size of components in actual implementation. In actual implementation, the type, quantity and proportion of each component can be changed at will, and the component layout type may also be more complicated.

[0032] Additionally, in the following description, specific details are provided to provide a thorough understanding of the examples. However, one skilled in the art will appreciate that the aspects described can be practiced without these specific details.

[0033] An embodiment of the present application provides an aircraft engine exhaust temperature warning system.

[0034] An aircraft engine exhaust temperature warning system comprises a processor, a wheel-load signal acquisition unit, an engine speed acquisition unit, a pressure altitude acquisition unit, an atmospheric static temperature acquisition unit, and an engine throttle acquisition unit; the wheel-load signal acquisition unit is used to acquire the aircraft's wheel-load signal from the landing gear system in the form of a switch signal; the engine speed acquisition unit is used to acquire the aircraft's engine speed from a speed signal converter in the form of a frequency quantity; the pressure altitude acquisition unit is used to acquire the aircraft's pressure altitude from a cabin pressure controller via a 429 bus; the atmospheric static temperature acquisition unit is used to acquire the atmospheric static temperature; and the engine throttle acquisition unit is used to acquire the aircraft's engine throttle angle in the form of an analog quantity from the aircraft's engine throttle's CD-1 angular displacement sensor.

[0035] like Figure 1 As shown, the processor is used to receive wheel load signals, engine speed, air pressure altitude, atmospheric static temperature, and engine throttle angle signals to determine whether the engine exhaust temperature exceeds the corresponding warning temperature under the current flight environment and flight state. The threshold value of the engine exhaust temperature warning is different in different flight environments and flight states.

[0036] When the aircraft is on the ground, that is, when the wheel load switch indicates ground:

[0037] When the engine speed is less than or equal to the preset speed ratio, the exhaust temperature warning temperature is the first warning temperature; when the engine speed is greater than the preset speed ratio, and the aircraft altitude is greater than or equal to the first preset altitude, the atmospheric static temperature is less than or equal to the first preset temperature, and the engine throttle angle is greater than or lower than the first preset angle, the exhaust temperature warning temperature is the second warning temperature; when any one of the three conditions of the aircraft altitude is greater than or equal to the first preset altitude, the atmospheric static temperature is less than or equal to the first preset temperature, and the engine throttle angle is greater than or lower than the first preset angle is not met: when the atmospheric static temperature is less than the second preset temperature, the exhaust temperature warning temperature is the third warning temperature, and when the atmospheric static temperature is greater than the third preset temperature, the exhaust temperature warning temperature is the fourth warning temperature, among which the first preset temperature is greater than the second preset temperature and less than the third preset temperature.

[0038] The preset speed ratio is 69.5%, the first alarm temperature is 690℃; the first preset altitude is 2000m, the first preset temperature is 16℃, the first preset angle is 84°, the second alarm temperature is 550℃; the second preset temperature is 15℃, the third alarm temperature is 520℃; the third preset temperature is 17℃, and the fourth alarm temperature is 570℃.

[0039] When the aircraft is in flight and the flight altitude is lower than the first flight altitude:

[0040] When the engine throttle angle is greater than or equal to 0° and less than or equal to the second preset angle, the exhaust temperature alarm temperature is the fifth alarm temperature; when the engine throttle angle is greater than the second preset angle and less than or equal to the first preset angle, the exhaust temperature alarm temperature is the sixth alarm temperature; when the engine throttle angle is greater than the first preset angle, the exhaust temperature alarm temperature is the seventh alarm temperature.

[0041] The second preset angle is 68°, the fifth alarm temperature is 500°C; the sixth alarm temperature is 540°C; and the seventh alarm temperature is 620°C.

[0042] When the aircraft is in flight and the flight altitude is greater than or equal to the second flight altitude:

[0043] When the engine throttle angle is greater than or equal to 0° and less than or equal to the second preset angle, the exhaust temperature warning temperature is the eighth warning temperature. When the engine throttle angle is greater than the second preset angle and less than or equal to the first preset angle, the exhaust temperature warning temperature is the ninth warning temperature. When the engine throttle angle is greater than the first preset angle, the exhaust temperature warning temperature is the tenth warning temperature. The eighth warning temperature is 520°C, the ninth warning temperature is 570°C, and the tenth warning temperature is 620°C.

[0044] The first preset altitude is 6500 meters and the second flight altitude is 6550 meters. To prevent the warning information from flashing frequently, when the aircraft rises from 6500 meters to 6550 meters, the range between 6500-6550 meters is set to less than 6500 meters. When the aircraft descends from 6550 meters to 6500 meters, the range between 6500-6550 meters is set to greater than or equal to 6550 meters.

[0045] For every 1°C increase in the aircraft's flight environment temperature compared to the standard temperature, the exhaust warning temperature will increase by 1°C accordingly; for every 1°C decrease in the aircraft's flight environment temperature compared to the standard temperature, the exhaust warning temperature will decrease by 1°C.

[0046] Different air engine exhaust temperature warning temperatures are designed according to different flight conditions and flight environments to improve the accuracy of the alarm. By collecting multiple parameters and making logical judgments, logical alarm states are realized with different colors and icon areas.

[0047] The above description is merely a specific embodiment of the present application, but the scope of protection of the present application is not limited thereto. Any changes or substitutions that can be easily conceived by a person skilled in the art within the technical scope disclosed in the present application should be included in the scope of protection of the present application. Therefore, the scope of protection of the present application should be based on the scope of protection of the claims.

Claims

1. An aircraft engine exhaust temperature warning system, characterized in that: It includes a processor, a wheel-load signal acquisition unit, an engine speed acquisition unit, a pressure altitude acquisition unit, an atmospheric static temperature acquisition unit and an engine throttle acquisition unit; the wheel-load signal acquisition unit is used to acquire the aircraft's wheel-load signal; the engine speed acquisition unit is used to acquire the aircraft's engine speed; the pressure altitude acquisition unit is used to acquire the aircraft's pressure altitude; the atmospheric static temperature acquisition unit is used to acquire the atmospheric static temperature; the engine throttle acquisition unit is used to acquire the aircraft's engine throttle angle; The processor is used to receive wheel load signals, engine speed, pressure altitude, atmospheric static temperature, and engine throttle angle signals to determine whether the engine exhaust temperature exceeds the corresponding warning temperature in the current flight environment and flight state. The threshold value of the engine exhaust temperature warning varies in different flight environments and flight states; When the aircraft is on the ground: When the engine speed is less than or equal to the preset speed ratio, the exhaust temperature warning temperature is the first warning temperature; When the engine speed is greater than the preset speed ratio, and the aircraft altitude is greater than or equal to the first preset altitude, the atmospheric static temperature is less than or equal to the first preset temperature, and the engine throttle angle is greater than or equal to the first preset angle, the exhaust temperature warning temperature is the second warning temperature; When any one of the following three conditions is not met: the aircraft altitude is greater than or equal to the first preset altitude, the atmospheric static temperature is less than or equal to the first preset temperature, and the engine throttle angle is greater than or equal to the first preset angle: when the atmospheric static temperature is less than the second preset temperature, the exhaust temperature alarm temperature is the third alarm temperature; when the atmospheric static temperature is greater than the third preset temperature, the exhaust temperature alarm temperature is the fourth alarm temperature, wherein the first preset temperature is greater than the second preset temperature and less than the third preset temperature.

2. The aircraft engine exhaust temperature warning system according to claim 1, characterized in that: The preset speed ratio is 69.5%, the first alarm temperature is 690℃; the first preset altitude is 2000m, the first preset temperature is 16℃, the first preset angle is 84°, the second alarm temperature is 550℃; the second preset temperature is 15℃, the third alarm temperature is 520℃; the third preset temperature is 17℃, and the fourth alarm temperature is 570℃.

3. The aircraft engine exhaust temperature warning system according to claim 2, characterized in that: When the aircraft is in flight and the flight altitude is lower than the first flight altitude: When the engine throttle angle is greater than or equal to 0° and less than or equal to the second preset angle, the exhaust temperature warning temperature is the fifth warning temperature; When the engine throttle angle is greater than the second preset angle and less than or equal to the first preset angle, the exhaust temperature warning temperature is the sixth warning temperature; When the engine throttle angle is greater than the first preset angle, the exhaust temperature warning temperature is the seventh warning temperature.

4. The aircraft engine exhaust temperature warning system according to claim 3, characterized in that: The second preset angle is 68°, the fifth alarm temperature is 500°C; the sixth alarm temperature is 540°C; and the seventh alarm temperature is 620°C.

5. The aircraft engine exhaust temperature warning system according to claim 4, characterized in that: When the aircraft is in flight and the flight altitude is greater than or equal to the second flight altitude: When the engine throttle angle is greater than or equal to 0° and less than or equal to the second preset angle, the exhaust temperature warning temperature is the eighth warning temperature; When the engine throttle angle is greater than the second preset angle and less than or equal to the first preset angle, the exhaust temperature warning temperature is the ninth warning temperature; When the engine throttle angle is greater than the first preset angle, the exhaust temperature warning temperature is the tenth warning temperature.

6. The aircraft engine exhaust temperature warning system according to claim 5, characterized in that: The eighth alarm temperature is 520°C, the ninth alarm temperature is 570°C, and the tenth alarm temperature is 620°C.

7. The aircraft engine exhaust temperature warning system according to claim 5, characterized in that: The first flight altitude is 6500 meters, the second flight altitude is 6550 meters, and when the aircraft rises from 6500 meters to 6550 meters, the range between 6500-6550 meters is set to less than 6500 meters, and when the aircraft descends from 6550 meters to 6500 meters, the range between 6500-6550 meters is set to greater than or equal to 6550 meters.

8. The aircraft engine exhaust temperature warning system according to any one of claims 1 to 7, characterized in that: For every 1°C increase in the aircraft's flight environment temperature compared to the standard temperature, the exhaust warning temperature will increase by 1°C accordingly; for every 1°C decrease in the aircraft's flight environment temperature compared to the standard temperature, the exhaust warning temperature will decrease by 1°C.

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