Propeller blade synchronous phasing using tone wheels
阅读说明:本技术 使用音轮的螺旋桨叶片同步定相 (Propeller blade synchronous phasing using tone wheels ) 是由 E.雅克波夫 J.R.雅沃 R.塔巴 于 2019-07-01 设计创作,主要内容包括:本发明涉及使用音轮的螺旋桨叶片同步定相。本文提供了用于对多发动机飞机进行同步定相的系统和方法。音轮被耦接到该飞机的第一发动机的第一螺旋桨。传感器被设置和构造成用于响应于该音轮上的第一和第二位置标记的通过而产生信号。控制系统被通信地耦接到该传感器用于获得该信号,并且构造成用于:确定该信号的两个后续信号脉冲之间的预期延迟;从该多个信号脉冲内识别与该第二位置标记相关联的特定脉冲;基于与该第二位置标记相关联的该特定脉冲产生的特定时间,来确定该第一螺旋桨的某一旋转位置在该特定时间对应于参考位置;以及基于该第一螺旋桨的该旋转位置,来执行针对该飞机的至少一个同步定相操作。(The invention relates to propeller blade synchronous phasing using tone wheels. Systems and methods for synchronously phasing multiple-engine aircraft are provided herein. A tone wheel is coupled to a first propeller of a first engine of the aircraft. A sensor is disposed and configured for generating a signal in response to the passage of the first and second position markers on the tone wheel. A control system is communicatively coupled to the sensor for obtaining the signal and configured for: determining an expected delay between two subsequent signal pulses of the signal; identifying a particular pulse associated with the second position marker from within the plurality of signal pulses; determining that a certain rotational position of the first propeller corresponds to a reference position at a particular time based on the particular time of generation of the particular pulse associated with the second position marker; and performing at least one synchronous phasing operation for the aircraft based on the rotational position of the first propeller.)
1. A system for synchronously phasing multiple-engine aircraft, comprising:
a tone wheel coupled to a first propeller of a first engine of the aircraft, the tone wheel including a plurality of circumferentially evenly spaced first position markers disposed on an outer circumferential surface of the tone wheel and a second position marker disposed on the outer surface, the second position marker disposed circumferentially closer to a selected one of the first position markers than the remaining first position markers and representing a reference position of the propeller, the tone wheel configured to rotate during operation of the first engine;
a sensor adjacent to the tone wheel and configured for generating a signal in response to passage of the first and second position markers, the signal comprising a plurality of signal pulses corresponding to the passage of the plurality of first and second position markers during rotation of the tone wheel; and
a control system communicatively coupled to the sensor for obtaining the signal and configured for:
determining an expected delay between two subsequent pulses of the plurality of signal pulses based on the plurality of signal pulses, the expected delay representing an interval of the plurality of first position markers;
identifying a particular pulse associated with the second position marker from within the plurality of signal pulses, the particular pulse having a delay shorter than the expected delay;
determining that a certain rotational position of the first propeller corresponds to the reference position at a particular time based on the particular time of generation of the particular pulse associated with the second position marker; and
performing at least one synchronous phasing operation for the aircraft based on the rotational position of the first propeller.
2. The system of claim 1, wherein the control system is configured to perform at least one synchronous phasing operation comprising:
transmitting a position signal representative of the rotational position of the first propeller to a central control device of the aircraft;
obtaining from the central control device an engine control signal generated by the central control device based on the position signal, the engine control signal including instructions for causing a predetermined operating parameter of at least one of the first engine and the first propeller to be adjusted to maintain a predetermined phase angle of the first propeller; and
adjusting at least one operating parameter of the at least one of the first engine and the first propeller based on the engine control signal.
3. The system of claim 2, wherein transmitting the position signal indicative of the rotational position of the first propeller to the central control device of the aircraft further causes the central control device to generate a command based on the position signal, the command for causing a predetermined operating parameter of at least one of a second engine and a second propeller of the aircraft to be adjusted to maintain a predetermined phase angle difference between the first propeller and the second propeller.
4. The system of claim 1, wherein the control system is a first control system, wherein the first control system is configured to perform at least one synchronous phasing operation comprising:
transmitting a position signal to a second control system associated with a second propeller of the aircraft;
obtaining from the second control system an engine control signal generated by the second control system based on the position signal, the engine control signal including instructions for causing a predetermined operating parameter of at least one of the first engine and the first propeller to be adjusted to maintain a predetermined phase angle of the first propeller; and
adjusting the predetermined operating parameter of the at least one of the first engine and the first propeller based on the engine control signal.
5. The system of claim 4, wherein transmitting the position signal indicative of the rotational position of the first propeller to the second control system further causes the second control system to generate a command based on the position signal, the command for causing a predetermined operating parameter of at least one of a second engine and a second propeller of the aircraft to be adjusted to maintain a predetermined phase angle difference between the first propeller and the second propeller.
6. The system of any one of claims 1 to 5, wherein the control system is further configured to:
obtaining at least one position signal from at least one supplemental control system, each of the at least one supplemental control system being associated with a respective supplemental engine and supplemental propeller of the aircraft, and each of the at least one position signal being indicative of a rotational position of a respective supplemental propeller of the aircraft;
generating at least one engine control signal based on the at least one position signal, the at least one engine control signal including instructions for causing a respective predetermined operating parameter of at least one of each supplemental engine and each supplemental propeller to be adjusted to maintain a predetermined phase angle difference between the first propeller and at least one supplemental propeller; and
each of the at least one engine control signal is communicated to a respective supplemental control system.
7. The system of any one of claims 1 to 5, wherein the control system is further configured to:
obtaining at least one position signal from at least one supplemental control system, each of the at least one supplemental control system being associated with a respective supplemental engine and supplemental propeller of the aircraft, and each of the at least one position signal being indicative of a rotational position of a respective supplemental propeller of the aircraft; and
adjusting a predetermined operating parameter of at least one of the first engine and the first propeller to maintain a predetermined phase angle difference between the first propeller and at least one supplemental propeller.
8. The system of claim 7, wherein the control system is further configured to:
generating at least one engine control signal based on the at least one position signal, the at least one engine control signal including instructions for causing a respective predetermined operating parameter of at least one of each supplemental engine and each supplemental propeller to be adjusted to maintain a predetermined phase angle difference between the first propeller and the at least one supplemental propeller; and
each of the at least one engine control signal is communicated to a respective supplemental control system.
9. The system of any one of claims 1 to 8, wherein the at least one synchronous phasing operation comprises adjusting at least one of a rotational speed of the first engine, a rotational speed of the first propeller, and a pitch of the first propeller.
10. The system of any of claims 1-9, wherein the second position marker is angled relative to the first position marker.
11. A method for performing synchronous phasing in a multi-engine aircraft, comprising:
obtaining, from a sensor adjacent to a tone wheel, a signal comprising a plurality of signal pulses generated in response to sensing the presence of a position marker disposed on an outer surface of the tone wheel of a first propeller coupled to a first engine of the aircraft, the tone wheel configured to rotate during operation of the first engine;
determining an expected delay between two subsequent signal pulses of the plurality of signal pulses based on the plurality of signal pulses, the expected delay representing an interval of a first plurality of position markers;
identifying a particular pulse within the plurality of signal pulses and associated with a second one of the position markers based on the expected delay;
determining, based on a particular time at which the particular pulse associated with the second position marker was generated, that a certain rotational position of the first propeller corresponds to a reference position of the first propeller associated with the second position marker at the particular time; and
performing at least one synchronous phasing operation for the engine based on the rotational position of the first propeller.
12. The method of claim 11, wherein performing at least one synchronous phasing operation comprises:
transmitting a position signal representative of the rotational position of the first propeller to a central control device of the aircraft;
obtaining from the central control device an engine control signal generated by the central control device based on the position signal, the engine control signal including instructions for causing a predetermined operating parameter of at least one of the first engine and the first propeller to be adjusted to maintain a predetermined phase angle of the first propeller; and
adjusting at least one operating parameter of the at least one of the first engine and the first propeller based on the engine control signal.
13. The method of claim 12, wherein transmitting the position signal indicative of the rotational position of the first propeller to the central control device of the aircraft further causes the central control device to generate a command based on the position signal, the command for causing a predetermined operating parameter of at least one of a second engine and a second propeller of the aircraft to be adjusted to maintain a predetermined phase angle difference between the first propeller and the second propeller.
14. The method of claim 11, wherein performing at least one synchronous phasing operation comprises:
transmitting a position signal to a second control system associated with a second propeller of the aircraft;
obtaining from the second control system an engine control signal generated by the second control system based on the position signal, the engine control signal including instructions for causing a predetermined operating parameter of at least one of the first engine and the first propeller to be adjusted to maintain a predetermined phase angle of the first propeller; and
adjusting the predetermined operating parameter of the at least one of the first engine and the first propeller based on the engine control signal.
15. The method of claim 14, wherein transmitting the position signal indicative of the rotational position of the first propeller to the second control system further causes the second control system to generate a command based on the position signal, the command for causing a predetermined operating parameter of at least one of a second engine and a second propeller of the aircraft to be adjusted to maintain a predetermined phase angle difference between the first propeller and the second propeller.
16. The method of any of claims 11 to 15, further comprising:
obtaining at least one position signal from at least one supplemental control system, each of the at least one supplemental control system being associated with a respective supplemental engine and supplemental propeller of the aircraft, and each of the at least one position signal being indicative of a rotational position of a respective supplemental propeller of the aircraft;
generating at least one engine control signal based on the at least one position signal, the at least one engine control signal including instructions for causing a respective predetermined operating parameter of at least one of each supplemental engine and each supplemental propeller to be adjusted to maintain a predetermined phase angle difference between the first propeller and at least one supplemental propeller; and
each of the at least one engine control signal is communicated to a respective supplemental control system.
17. The method of any of claims 11 to 15, further comprising:
obtaining at least one position signal from at least one supplemental control system, each of the at least one supplemental control system being associated with a respective supplemental engine and supplemental propeller of the aircraft, and each of the at least one position signal being indicative of a rotational position of a respective supplemental propeller of the aircraft; and
adjusting a predetermined operating parameter of at least one of the first engine and the first propeller to maintain a predetermined phase angle difference between the first propeller and at least one supplemental propeller.
18. The method of claim 17, further comprising:
generating at least one engine control signal based on the at least one position signal, the at least one engine control signal including instructions for causing a respective predetermined operating parameter of at least one of each supplemental engine and each supplemental propeller to be adjusted to maintain a predetermined phase angle difference between the first propeller and the at least one supplemental propeller; and
each of the at least one engine control signal is communicated to a respective supplemental control system.
19. The method of any one of claims 11 to 18, wherein performing the at least one synchronous phasing operation comprises performing adjusting at least one of a rotational speed of the first engine, a rotational speed of the first propeller, and a pitch of the first propeller.
20. The method of any of claims 11 to 19, wherein the second position marker is angled relative to a position marker of the first plurality of position markers.
Technical Field
The present disclosure relates generally to engines and, more particularly, to a propeller control system for a gas turbine engine.
Background
Certain types of phonic wheels (phonic wheels) may be used to provide information about the relative phase of the propellers of a turboprop, typically by removing one of the markers, thereby producing a detectable "missing tooth", or by adding additional markers that are distinguishable from the other markers. Knowledge of the relative phase of the propellers can be used to perform synchronous phasing (synchronization), a technique for reducing vibration and noise experienced by passengers of an aircraft. However, synchronous phasing techniques based on missing teeth tend to be inaccurate and may require additional equipment to function properly.
Therefore, there is a need for an improved solution.
Disclosure of Invention
According to one broad aspect, there is provided a system for synchronously phasing multiple-engine aircraft, comprising: a tone wheel coupled to a first propeller of a first engine of the aircraft, the tone wheel including a plurality of circumferentially evenly spaced first position markers disposed on an outer circumferential surface of the tone wheel and a second position marker disposed on the outer surface, the second position marker disposed circumferentially closer to a selected one of the first position markers than the remaining first position markers and representing a reference position of the propeller, the tone wheel configured to rotate during operation of the first engine; a sensor adjacent to the tone wheel and configured for generating a signal in response to passage of the first and second position markers, the signal comprising a plurality of signal pulses corresponding to the passage of the plurality of first and second position markers during rotation of the tone wheel; and a control system communicatively coupled to the sensor for obtaining the signal and configured for: determining an expected delay between two subsequent pulses of the plurality of signal pulses based on the plurality of signal pulses, the expected delay representing an interval of the plurality of first position markers; identifying a particular pulse associated with the second position marker from within the plurality of signal pulses, the particular pulse having a delay shorter than the expected delay; determining that a certain rotational position of the first propeller corresponds to the reference position at a particular time based on the particular time of generation of the particular pulse associated with the second position marker; and performing at least one synchronous phasing operation for the aircraft based on the rotational position of the first propeller.
In some embodiments, the control system is configured for performing at least one synchronous phasing operation comprising: transmitting a position signal representative of the rotational position of the first propeller to a central control device of the aircraft; obtaining from the central control device an engine control signal generated by the central control device based on the position signal, the engine control signal including instructions for causing a predetermined operating parameter of at least one of the first engine and the first propeller to be adjusted to maintain a predetermined phase angle of the first propeller; and adjusting at least one operating parameter of the at least one of the first engine and the first propeller based on the engine control signal.
In some embodiments, transmitting the position signal indicative of the rotational position of the first propeller to the central control device of the aircraft further causes the central control device to generate instructions based on the position signal for causing a predetermined operating parameter of at least one of a second engine and a second propeller of the aircraft to be adjusted to maintain a predetermined phase angle difference between the first propeller and the second propeller.
In some embodiments, the control system is a first control system, wherein the first control system is configured for performing at least one synchronous phasing operation comprising: transmitting a position signal to a second control system associated with a second propeller of the aircraft; obtaining from the second control system an engine control signal generated by the second control system based on the position signal, the engine control signal including instructions for causing a predetermined operating parameter of at least one of the first engine and the first propeller to be adjusted to maintain a predetermined phase angle of the first propeller; and adjusting the predetermined operating parameter of the at least one of the first engine and the first propeller based on the engine control signal.
In some embodiments, transmitting the position signal indicative of the rotational position of the first propeller to the second control system further causes the second control system to generate instructions based on the position signal for causing a predetermined operating parameter of at least one of a second engine and a second propeller of the aircraft to be adjusted to maintain a predetermined phase angle difference between the first propeller and the second propeller.
In some embodiments, the control system is further configured for: obtaining at least one position signal from at least one supplemental control system, each of the at least one supplemental control system being associated with a respective supplemental engine and supplemental propeller of the aircraft, and each of the at least one position signal being indicative of a rotational position of a respective supplemental propeller of the aircraft; generating at least one engine control signal based on the at least one position signal, the at least one engine control signal including instructions for causing a respective predetermined operating parameter of at least one of each supplemental engine and each supplemental propeller to be adjusted to maintain a predetermined phase angle difference between the first propeller and at least one supplemental propeller; and communicating each of the at least one engine control signal to a respective supplemental control system.
In some embodiments, the control system is further configured for: obtaining at least one position signal from at least one supplemental control system, each of the at least one supplemental control system being associated with a respective supplemental engine and supplemental propeller of the aircraft, and each of the at least one position signal being indicative of a rotational position of a respective supplemental propeller of the aircraft; and adjusting a predetermined operating parameter of at least one of the first engine and the first propeller to maintain a predetermined phase angle difference between the first propeller and at least one supplemental propeller.
In some embodiments, the control system is further configured for: generating at least one engine control signal based on the at least one position signal, the at least one engine control signal including instructions for causing a respective predetermined operating parameter of at least one of each supplemental engine and each supplemental propeller to be adjusted to maintain a predetermined phase angle difference between the first propeller and the at least one supplemental propeller; and communicating each of the at least one engine control signal to a respective supplemental control system.
In some embodiments, the at least one synchronous phasing operation comprises adjusting at least one of a rotational speed of the first engine, a rotational speed of the first propeller, and a pitch of the first propeller.
In some embodiments, the second position marker is angled relative to the first position marker.
According to another broad aspect, there is provided a method for performing synchronous phasing in a multi-engine aircraft, comprising: obtaining, from a sensor adjacent to a tone wheel, a signal comprising a plurality of signal pulses generated in response to sensing the presence of a position marker disposed on an outer surface of the tone wheel of a first propeller coupled to a first engine of the aircraft, the tone wheel configured to rotate during operation of the first engine; determining an expected delay between two subsequent signal pulses of the plurality of signal pulses based on the plurality of signal pulses, the expected delay representing an interval of a first plurality of position markers; identifying a particular pulse within the plurality of signal pulses and associated with a second one of the position markers based on the expected delay; determining, based on a particular time at which the particular pulse associated with the second position marker was generated, that a certain rotational position of the first propeller corresponds to a reference position of the first propeller associated with the second position marker at the particular time; and performing at least one synchronous phasing operation for the engine based on the rotational position of the first propeller.
In some embodiments, performing at least one synchronous phasing operation comprises: transmitting a position signal representative of the rotational position of the first propeller to a central control device of the aircraft; obtaining from the central control device an engine control signal generated by the central control device based on the position signal, the engine control signal including instructions for causing a predetermined operating parameter of at least one of the first engine and the first propeller to be adjusted to maintain a predetermined phase angle of the first propeller; and adjusting at least one operating parameter of the at least one of the first engine and the first propeller based on the engine control signal.
In some embodiments, transmitting the position signal indicative of the rotational position of the first propeller to the central control device of the aircraft further causes the central control device to generate instructions based on the position signal for causing a predetermined operating parameter of at least one of a second engine and a second propeller of the aircraft to be adjusted to maintain a predetermined phase angle difference between the first propeller and the second propeller.
In some embodiments, performing at least one synchronous phasing operation comprises: transmitting a position signal to a second control system associated with a second propeller of the aircraft; obtaining from the second control system an engine control signal generated by the second control system based on the position signal, the engine control signal including instructions for causing a predetermined operating parameter of at least one of the first engine and the first propeller to be adjusted to maintain a predetermined phase angle of the first propeller; and adjusting the predetermined operating parameter of the at least one of the first engine and the first propeller based on the engine control signal.
In some embodiments, transmitting the position signal indicative of the rotational position of the first propeller to the second control system further causes the second control system to generate instructions based on the position signal for causing a predetermined operating parameter of at least one of a second engine and a second propeller of the aircraft to be adjusted to maintain a predetermined phase angle difference between the first propeller and the second propeller.
In some embodiments, the method further comprises: obtaining at least one position signal from at least one supplemental control system, each of the at least one supplemental control system being associated with a respective supplemental engine and supplemental propeller of the aircraft, and each of the at least one position signal being indicative of a rotational position of a respective supplemental propeller of the aircraft; generating at least one engine control signal based on the at least one position signal, the at least one engine control signal including instructions for causing a respective predetermined operating parameter of at least one of each supplemental engine and each supplemental propeller to be adjusted to maintain a predetermined phase angle difference between the first propeller and at least one supplemental propeller; and communicating each of the at least one engine control signal to a respective supplemental control system.
In some embodiments, the method further comprises: obtaining at least one position signal from at least one supplemental control system, each of the at least one supplemental control system being associated with a respective supplemental engine and supplemental propeller of the aircraft, and each of the at least one position signal being indicative of a rotational position of a respective supplemental propeller of the aircraft; and adjusting a predetermined operating parameter of at least one of the first engine and the first propeller to maintain a predetermined phase angle difference between the first propeller and at least one supplemental propeller.
In some embodiments, the method further comprises: generating at least one engine control signal based on the at least one position signal, the at least one engine control signal including instructions for causing a respective predetermined operating parameter of at least one of each supplemental engine and each supplemental propeller to be adjusted to maintain a predetermined phase angle difference between the first propeller and the at least one supplemental propeller; and communicating each of the at least one engine control signal to a respective supplemental control system.
In some embodiments, performing the at least one synchronous phasing operation comprises performing adjusting at least one of a rotational speed of the first engine, a rotational speed of the first propeller, and a pitch of the first propeller.
In some embodiments, the second position marker is angled relative to a position marker of the first plurality of position markers.
According to the embodiments described herein, the features of the systems, devices, and methods described herein may be used in various combinations.
Drawings
Referring now to the drawings wherein:
FIG. 1 is a schematic cross-sectional view of an exemplary gas turbine engine;
FIG. 2 is a schematic diagram of an exemplary system for sensing a tone wheel;
FIG. 3 is a schematic view of the propeller of FIG. 1 with the tone wheel of FIG. 2 in accordance with one embodiment;
FIG. 4 is a schematic top view of one embodiment of the tone wheel of FIG. 2;
FIG. 5 is a flow chart of an exemplary method for monitoring vibrations in an engine; and
6A-B are block diagrams of an exemplary multi-engine aircraft;
FIG. 7 is a block diagram of an exemplary computer system for implementing part or all of the method of FIG. 5.
It will be noted that throughout the drawings, like features are indicated by like reference numerals.
Detailed Description
FIG. 1 depicts a
The turbine section 118 includes: a
The rotor in the form of a
Referring to fig. 2, a
The
The
In the example shown in fig. 3, a side view of a portion of tone wheel 104 and
In some embodiments, a
Referring to fig. 3, in some embodiments,
In some embodiments, the position markers may be applied to the
With continued reference to fig. 3,
As depicted in fig. 3, the
Referring to fig. 4, one embodiment of
In fig. 4, a top view of a portion of
In the embodiment depicted in fig. 4, the
In some embodiments,
In one example,
Although the preceding paragraphs have focused on the use of a
The signal pulses generated by
Referring to fig. 5, a
At
For example, a portion of the signal generated by the
At
In the case of the
At
Since the particular signal pulse is associated with
In some embodiments, when the
Other methods for determining the phase of the
At
As part of the synchronous phasing operation of
Referring to fig. 6A-B, different examples of synchronous phasing operations for a
In fig. 6A, the
In one example, the
In fig. 6B,
In one example,
Additionally, in some embodiments, the
It should be noted that although the examples of fig. 6A-B discussed above relate to a
Referring to FIG. 7, the
Memory 714 may include any suitable known or other machine-readable storage medium. Memory 714 may include a non-transitory computer readable storage medium, such as, but not limited to, an electronic, magnetic, optical, electromagnetic, infrared, or semiconductor system, apparatus, or device, or any suitable combination of the foregoing. The memory 714 may comprise any type of suitable combination of computer memory, internal or external to the device, such as Random Access Memory (RAM), Read Only Memory (ROM), Compact Disc Read Only Memory (CDROM), electro-optic memory, magneto-optic memory, Erasable Programmable Read Only Memory (EPROM) and Electrically Erasable Programmable Read Only Memory (EEPROM), ferroelectric RAM (fram), and the like. Memory 714 may include any storage (e.g., device) suitable for retrievably storing machine-readable instructions 716 that are executable by processing unit 712.
It should be noted that the
The systems and methods described herein may be implemented in a high level procedural or object oriented programming or scripting language, or a combination thereof, to communicate with or facilitate the operation of a computer system, such as
Computer-executable instructions may take many forms, including program modules, executed by one or more computers or other devices. Generally, program modules include routines, programs, objects, components, data structures, etc. that perform particular tasks or implement particular abstract data types. Generally, the functionality of the program modules may be combined or distributed as desired in various embodiments.
The above description is intended to be exemplary only, and those skilled in the art will recognize that changes may be made to the embodiments described without departing from the scope of the invention disclosed. Still other modifications that fall within the scope of the invention will be apparent to those skilled in the art upon review of this disclosure.
Various aspects of the systems and methods described herein may be used alone, in combination, or in a variety of arrangements not specifically discussed in the embodiments described in the foregoing and is therefore not limited in its application to the details and arrangement of components set forth in the foregoing description or illustrated in the drawings. For example, aspects described in one embodiment may be combined in any manner with aspects described in other embodiments. While particular embodiments have been shown and described, it will be obvious to those skilled in the art that changes and modifications may be made without departing from the invention in its broader aspects. The scope of the appended claims should not be limited to the embodiments set forth in the examples, but should be given the broadest reasonable interpretation consistent with the description as a whole.
- 上一篇:一种医用注射器针头装配设备
- 下一篇:飞机发动机喘振识别方法