CN112066413B - Gas turbine, combustor, monitoring device and monitoring method for oscillatory combustion, and computer-readable storage medium - Google Patents
Gas turbine, combustor, monitoring device and monitoring method for oscillatory combustion, and computer-readable storage medium Download PDFInfo
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- CN112066413B CN112066413B CN201910496285.5A CN201910496285A CN112066413B CN 112066413 B CN112066413 B CN 112066413B CN 201910496285 A CN201910496285 A CN 201910496285A CN 112066413 B CN112066413 B CN 112066413B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
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- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
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Abstract
The invention provides a monitoring method of oscillatory combustion, a computer readable storage medium, a monitoring device of oscillatory combustion, a combustion chamber and a gas turbine. The monitoring method comprises the steps of collecting static pressure of air inlet of a flame tube of a combustion chamber and static pressure inside the flame tube to obtain pressure drop of the air inlet of the flame tube; comparing the intake pressure drop with a corresponding threshold value, judging whether the intake pressure drop reaches the threshold value, and if so, identifying that the current state is an oscillatory combustion state; and if not, identifying the current state as a stable combustion state.
Description
Technical Field
The invention relates to a gas turbine, a combustor, a monitoring device of oscillatory combustion, a monitoring method and a computer readable storage medium.
Background
In order to meet the airworthiness requirement, the aero-engine adopts the lean oil combustion technology to reduce NOxWhile lean combustion tends to initiate oscillatory combustion, it can be severe enough to cause ablation of the hot end components of the combustion chamber. In addition, to reduce NOxTo exhaust, more air needs to be distributed to the head of the combustion chamber to lower the equivalence ratio of the combustion zone, while the liner cooling air is reduced, the acoustic impedance of the liner walls is increased, and the degree of oscillatory combustion is also exacerbated.
At present, in order to inhibit the oscillatory combustion, more fuel is supplied to the pre-combustion stage by adjusting the fuel distribution ratio so as to enhance the stability of flame; this requires that the stable combustion boundary of the combustion chamber be explored in advance through a large number of tests.
The method is characterized in that an active control method is adopted in a combustion chamber of the ground industrial gas turbine to inhibit oscillatory combustion, particularly, a dynamic diagnosis system is used for monitoring pulsating pressure in the combustion chamber in real time and feeding back a signal to a dynamic database system, the dynamic database system judges whether oscillatory combustion occurs or not, and if the oscillatory combustion occurs, a control system adjusts the proportion of class-class fuel until the oscillatory combustion disappears.
For civil turbofan aircraft engines, currently, no proven engine adopts a dynamic pressure measurement system to directly monitor the oscillatory combustion in a combustion chamber, and the running data is checked through a health management system and a database to judge whether the running states of the engine and all parts of the engine are normal. The main reason is that the high temperature measurement environment on an aircraft engine can attenuate the dynamic pressure amplitude too much, resulting in inaccurate or erroneous measurements. The problems brought by not adopting a dynamic pressure measuring system are that: the working environment of the aircraft engine is very complicated, even if a large number of flight tests are carried out before the aircraft is suitable for navigation and evidence collection, the tests cannot completely simulate the all-weather working environment, and a test database has certain limitation. Although a scheme of indirectly diagnosing the oscillating combustion of the combustion chamber by using a mechanical vibration sensor of the engine is also provided, the pressure wave action of an air passage in the combustion chamber is used on a flame tube assembly, the air passage fluctuation is changed into mechanical vibration and then is transmitted to the vibration sensor through a structural assembly, the damping factor in the process is related to the structural configuration of the engine, the structural connection mode of the assembly and the load stress path, and the problem of signal attenuation also exists. Once intense combustion in the combustion chamber occurs, the hot end components are likely to be damaged, generally only within tens of seconds.
Disclosure of Invention
It is an object of the present invention to provide a method of monitoring combustion oscillations.
It is another object of the present invention to provide a computer-readable storage medium.
It is another object of the present invention to provide a monitoring device for oscillating combustion.
It is another object of the present invention to provide a combustion chamber.
It is another object of the present invention to provide a gas turbine.
A monitoring method of oscillatory combustion according to an aspect of the present invention includes:
collecting the static pressure of air inlet of a flame tube of a combustion chamber and the static pressure in the flame tube;
obtaining the intake pressure drop of the flame tube according to the intake static pressure of the flame tube and the internal static pressure of the flame tube, comparing the intake pressure drop with a corresponding threshold value, judging whether the intake pressure drop reaches the threshold value, and if so, identifying that the current state is an oscillation combustion state; and if not, identifying the current state as a stable combustion state.
In an embodiment of the monitoring method, the intake pressure drop of the combustor basket includes one or more of the following values:
the outer ring air inlet pressure drop is the static pressure of the outer ring cavity of the flame tube, and the outer ring air inlet pressure drop is the difference value of the static pressure of the outer ring cavity of the flame tube and the internal static pressure of the flame tube, or the ratio of the difference value to the static pressure of the outer ring cavity of the flame tube or the internal static pressure of the flame tube;
the inner ring air inlet pressure drop is the static pressure of the inner ring cavity of the flame tube, and the inner ring air inlet pressure drop is the difference value of the static pressure of the inner ring cavity of the flame tube and the static pressure inside the flame tube, or the ratio of the difference value to the static pressure of the inner ring cavity of the flame tube or the static pressure of the inner ring part of the flame tube;
and the head air inlet pressure drop is the static pressure of the diffuser air outlet of the combustion chamber or the static pressure of the flame tube head air inlet, and the head air inlet pressure drop is the difference value of the static pressure of the diffuser air outlet of the combustion chamber or the static pressure of the flame tube head air inlet and the static pressure in the flame tube, or the ratio of the difference value to the static pressure of the diffuser air outlet or the static pressure of the flame tube head air inlet or the static pressure in the flame tube.
In an embodiment of the monitoring method, the threshold includes a threshold of a rate of change of the intake pressure drop with time and a threshold of the number of times the intake pressure drop reaches an oscillatory combustion value, and the oscillatory combustion value is an intake pressure drop value corresponding to a combustion chamber structure and a working condition, where oscillatory combustion occurs.
A computer readable storage medium according to another aspect of the present invention has stored thereon computer instructions which, when executed by a processor, perform the steps of:
the method comprises the steps of obtaining the intake pressure drop of a flame tube according to the collected intake static pressure of the flame tube of the combustion chamber and the static pressure in the flame tube, comparing the intake pressure drop with a corresponding threshold value, judging whether the intake pressure drop reaches the threshold value, identifying the current state as an oscillatory combustion state if the intake pressure drop reaches the threshold value, identifying the current state as a stable combustion state if the intake pressure drop does not reach the threshold value, and outputting a corresponding oscillatory combustion state signal or a corresponding stable combustion signal.
According to another aspect of the invention, a monitoring device for oscillatory combustion comprises a processor and the computer readable storage medium.
According to another aspect of the present invention, a monitoring apparatus for oscillating combustion includes:
the signal acquisition module at least acquires intake static pressure of a flame tube of the combustion chamber and internal static pressure of the flame tube;
the analysis and judgment module is used for obtaining the intake pressure drop of the flame tube according to the intake static pressure and the static pressure in the flame tube, comparing the intake pressure drop with a corresponding threshold value, judging whether the intake pressure drop reaches the threshold value, and if so, identifying the current state as the oscillation combustion state; and if not, identifying the current state as a stable combustion state.
In an embodiment of the monitoring device, the signal acquisition module includes a pressure sensor for sensing a static pressure value and converting the static pressure value into an analog electrical signal, and an analog/digital converter for converting the analog electrical signal into a digital signal, and the digital signal is output to the analysis and judgment module.
In an embodiment of the monitoring device, the monitoring device includes a database, the database stores a plurality of thresholds corresponding to a plurality of combustion chamber structures and working conditions and generating oscillatory combustion, and the analysis and judgment module retrieves the thresholds to compare the intake pressure drop with the corresponding thresholds.
According to another aspect of the invention, a combustion chamber is provided having a static pressure measurement point for measuring intake static pressure and flame tube internal static pressure.
In an embodiment of the combustion chamber, the plurality of static pressure measurement points are located in one or more of the following first, second, and third regions:
in the first region, at least one static pressure measuring point is positioned in an outer ring cavity of the flame tube, and at least one static pressure measuring point is positioned in an outer ring part of the flame tube or an inner ring part of the flame tube so as to measure the static pressure of the outer ring cavity of the flame tube and the static pressure in the flame tube;
in the second area, at least one static pressure measuring point is positioned in an inner ring cavity of the flame tube, and at least one static pressure measuring point is positioned in the outer ring part of the flame tube or the inner ring part of the flame tube so as to measure the static pressure of the inner ring cavity of the flame tube and the static pressure in the flame tube;
and in the third area, at least one static pressure measuring point is positioned at a diffuser air outlet of the combustion chamber or an air inlet at the head part of the flame tube, and at least one static pressure measuring point is positioned at an outer ring part of the flame tube or an inner ring part of the flame tube so as to measure the static pressure of the diffuser air outlet of the combustion chamber or the static pressure of the air inlet at the head part of the flame tube and the static pressure in the flame tube.
According to another aspect of the invention, a gas turbine comprises the monitoring device for oscillatory combustion described in any one of the above or the combustion chamber described in any one of the above.
The invention has the advantages that the intake pressure drop of the flame tube is used as a monitoring parameter to monitor and judge the oscillatory combustion, and the static pressure measurement mode is adopted, so that the defect of amplitude attenuation of dynamic pressure measurement is avoided, the requirements on a sensor and a data acquisition and control system are reduced, the cost of a monitoring device is reduced, and the reliability and the service life of the whole monitoring system are improved. Meanwhile, by reliably monitoring the oscillatory combustion, the prompt that the oil supply rule of the engine needs to be adjusted can be provided for an operator in time, and the safety of the operation of the gas turbine and the combustion chamber can be ensured in the operation process.
Drawings
In order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in detail below, wherein:
FIG. 1 is a schematic view of the combustion chamber structure of an embodiment showing the air flow in steady state.
FIG. 2 is a schematic view of the air flow of an embodiment of the combustion chamber configuration in a combustion oscillation state.
FIG. 3 is a graph of pulsating pressure and combustor via pressure drop as a function of acoustic throttling effect.
FIG. 4 is a schematic structural diagram of an embodiment of measuring a static pressure difference value between an outer ring cavity and an outer ring part of a flame tube.
FIG. 5 is a schematic diagram of a measurement configuration for measuring static pressure according to an embodiment.
FIG. 6 is a flow chart illustrating a method for monitoring combustion oscillations according to one embodiment.
Detailed Description
In order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in detail below.
In the following description, numerous specific details are set forth in order to provide a thorough understanding of the present invention, but the present invention may be practiced in other ways than those specifically described herein, and thus the present invention is not limited to the specific embodiments disclosed below.
As used in this application and the appended claims, the terms "a," "an," "the," and/or "the" are not intended to be inclusive in the singular, but rather are intended to be inclusive in the plural unless the context clearly dictates otherwise. In general, the terms "comprises" and "comprising" merely indicate that steps and elements are included which are explicitly identified, that the steps and elements do not form an exclusive list, and that a method or apparatus may include other steps or elements. Also, the present application uses specific words to describe embodiments of the application.
Furthermore, each of the embodiments described below has one or more technical features, and thus, the use of the technical features of any one embodiment does not necessarily mean that all of the technical features of any one embodiment are implemented at the same time or that only some or all of the technical features of different embodiments are implemented separately. In other words, those skilled in the art can selectively implement some or all of the features of any embodiment or combinations of some or all of the features of multiple embodiments according to the disclosure of the present invention and according to design specifications or implementation requirements, thereby increasing the flexibility in implementing the invention.
These and other features and characteristics of the present invention, as well as the methods of operation and functions of the related elements of structure and the combination of parts and economies of manufacture, will become more apparent upon consideration of the following detailed description with reference to the accompanying drawings, all of which form a part of this specification. It is to be expressly understood, however, that the drawings are for the purpose of illustration and description only and are not intended as a definition of the limits of the invention. It should be understood that all of the accompanying drawings are not to scale.
Referring to fig. 1, 2 and 4, the combustion chamber structure of the gas turbine is shown to include a front diffuser 1, an outer casing 2, an inner casing 9, a liner head 8, a fuel nozzle 3, an ignition electric nozzle 5, a liner outer ring part 6 and a liner inner ring part 11; the head part 8 can adopt a gas inlet structure comprising a swirler, and the outer ring part 6 and the inner ring part 11 of the flame tube can adopt a gas film cooling mode. Under the stable combustion state, the air flows out from the gas outlet 7 of leading diffuser 1, falls into three and gets into inside the flame tube, and the flame tube holds chamber 12 promptly:
A) through the air flow path 100 through the air inlet swirler passages of the liner head 8 into the liner pocket 12;
B) enters the combustor basket cavity 12 through the air flow path 200 through the cooling holes of the combustor basket outer ring part 6;
C) enters the combustor basket cavity 12 through the cooling holes of the combustor basket inner ring portion 11 via the air flow path 300.
Therefore, the static pressure of the liner may be represented by the intake portion corresponding to a), B), and C), for example, in conjunction with fig. 1 and 4, the static pressure of the liner may be represented by the static pressure of the outlet of the combustor diffuser 1 or the static pressure of the inlet of the liner head 8 corresponding to a), or may be represented by the static pressure of the liner outer annular chamber 4 corresponding to B), or may be represented by the static pressure of the liner inner annular chamber 10 corresponding to C). It will be appreciated that the representation of intake static pressure is not limited to the static pressure in the above described position.
Further, the inlet pressure drop of the liner may be represented by one or more of the following parameters:
the intake pressure drop of the air flow path 100 corresponding to a) above may be referred to as a head intake pressure drop, and may be a static pressure at the air outlet 7 of the diffuser 1 of the combustion chamber, or a difference between an intake static pressure at the liner head 8 and a static pressure in the liner cavity 12, or a ratio of the difference to a static pressure at the air outlet 7 of the diffuser 1 of the combustion chamber, or an intake static pressure at the liner head 8 or a static pressure in the liner cavity 12;
the intake pressure drop of the air flow path 200 corresponding to the above B), referred to as outer ring intake pressure drop, may be a difference between the static pressure of the liner outer annular chamber 4 and the static pressure of the liner accommodating chamber 12, or a ratio of the difference to the static pressure of the liner outer annular chamber 4 or the static pressure of the liner accommodating chamber 12;
the intake pressure drop of the air flow path 300 corresponding to C) may be a difference between the static pressure of the inner liner annular chamber 10 and the static pressure of the liner accommodating chamber 12, or a ratio of the difference to the static pressure of the inner liner annular chamber 10 or the static pressure of the liner accommodating chamber 12.
Referring to fig. 4, in one embodiment, the intake pressure drop of the flame tube is measured, and static pressure measuring points for measuring intake static pressure and static pressure inside the flame tube are arranged in the combustion chamber. For example, in the embodiment shown in fig. 4, a static pressure measuring point 13 is provided in the liner outer annular cavity 4 to measure the outer annular cavity static pressure, and a static pressure measuring point 14 is provided in the liner outer annular portion 6 to measure the liner accommodating cavity 12, that is, the static pressure inside the liner, it can be understood that the measuring point for measuring the static pressure of the liner accommodating cavity 12 is not necessarily provided in the liner outer annular portion 6, but may also be provided in the liner inner annular portion 9, the difference between the two in actual measurement is negligible, and can represent the static pressure of the liner accommodating cavity 12, or the static pressure measuring point is provided at other positions to measure the static pressure inside the liner, in short, the position shown in fig. 4 is not used as a limitation, this arrangement structure is marked as the static pressure measuring point is provided in the first region, the measurement result is collected, and the outer ring intake pressure drop corresponding to the air flow path 200 can be further calculated. The static pressure measuring points 13 and 14 may be one or more, that is, a plurality of static pressure measuring points may measure the static pressure of the outer ring cavity of the flame tube and the static pressure inside the flame tube, which is not limited to the content shown in fig. 4. It can be understood that a static pressure measuring point may also be provided in the inner ring cavity 10 of the liner to measure the static pressure in the inner ring cavity 10 of the liner, and a static pressure measuring point may be provided in the inner ring portion 9 or the outer ring portion 6 of the liner to measure the static pressure in the liner, and this arrangement structure is recorded as providing a static pressure measuring point in the second region, and collecting the measurement result, the inner ring intake pressure drop corresponding to the air flow path 300 may be further calculated. Or a static pressure measuring point can be arranged at the air outlet 7 of the diffuser 1 of the combustion chamber or the air inlet of the flame tube head 8 to measure the static pressure at the air outlet of the diffuser 1 of the combustion chamber or the static pressure at the air inlet of the flame tube head 8, and a static pressure measuring point is arranged at the inner ring part 9 or the outer ring part 6 of the flame tube to measure the static pressure in the flame tube, and the arrangement structure is marked that a static pressure measuring point is arranged in the third area, and the measurement result is collected, so that the head intake pressure drop corresponding to the air flow path 100 can be further calculated. As shown in fig. 4, the static pressure measuring point 13 is arranged in the outer ring cavity 4 of the flame tube, and the static pressure measuring point 14 is arranged in the outer ring part 6 of the flame tube, so that the combustion chamber of the gas turbine is generally provided with the static pressure measuring point 13 in the outer ring cavity 4 of the flame tube, and the static pressure measuring points are additionally arranged on the outer ring part 6 of the flame tube on the basis of the static pressure measuring point 13, so that the positions are relatively close to each other, the precious sensor arrangement space in combustion is saved, the structural change of the existing combustion chamber is small, the design and processing difficulty of the combustion chamber structure and a control system of oscillatory combustion is reduced, and the cost is reduced.
The specific static pressure measurement structure of the static pressure measurement point can be exemplified by the static pressure measurement structure of the static pressure measurement point of the outer ring part 6 of the flame tube shown in fig. 5, and the static pressure of the outer ring part 6 of the flame tube is led out and measured through the static pressure sensing part 17; the static pressure sensing part 17 is arranged on the outer casing 2 by adopting a threaded connection or other connection modes; the static pressure sensing part 17 passes through the outer ring part 6 of the flame tube through the floating sleeve 15; the floating sleeve 15 is mounted on a mounting 16 on the outer ring portion 6 of the liner. It is understood that other static pressure measurement configurations may be used by those skilled in the art for measurement and are not limited to the static pressure measurement configuration shown in fig. 5.
The principle of identifying oscillatory combustion by intake pressure drop determination is that, with reference to FIG. 3, FIG. 3 is the inventor's discovery of the acoustic throttling effect of the cooling holes of the combustor liner assembly, with the ordinate being the actual via pressure drop Δ P and the mean pressure P of the liner pocket 124To the power of 3/2, i.e. of
The abscissa is the pulsating pressure amplitude | P 'of the liner cavity 12'4(amplitude corresponding to main frequency after Fourier transform) and average pressure P4Is a percentage of
Since the flow mach number in the combustion chamber is generally 0.2 or less, the pressure drop in the intake passage at each point in the combustion chamber is normal (for example, in the case of non-oscillatory combustion)
Determined by its flow resistance characteristics, i.e. only with the effective area ACdAnd intake air composition parameter
In connection with, wherein, W31Is the inlet flow of the flame tube head, T31Is the inlet air temperature of the head of the flame tube, P31The air inlet pressure of the head of the flame tube; if it is
Without change, the voltage drop is controlled by ACdAnd (6) determining. FIG. 2 shows that
Under the condition of no change, the fuel-air ratio is increased, so that the combustion chamber generates oscillation combustion, and the oscillation amplitude is increased along with the increase of the fuel-air ratio, so that the combustion chamber pressure drop observed in the test is changed along with the oscillation amplitude. Test data analysis results show that the cooling pore passage of the flame tube is throttled under the condition of the sound field of oscillatory combustion, so that the AC of the cooling gas of the flame tubedReduced, total combustion chamber flow ACdDecreasing, resulting in an increase in combustion chamber pressure drop. The oblique lines in the figure represent the pulsating pressure amplitude corresponding to the trigger throttling effect; in the range of the upper left side of the oblique line (y is equal to x in the figure), the pulsating pressure cannot change the pressure drop of the combustion chamber, in the range of the lower right side of the oblique line, the pulsating pressure can cause the pressure drop of the combustion chamber to increase, when the pulsating pressure increases to a certain degree, the air inlet of the flame tube is completely blocked, and all the air inlet can only enter the flame tube from the head. By theoretical derivation, the triggering conditions for acoustic throttling can be derived as follows:
wherein, P'4Is the amplitude of the pulsating pressure in the flame tube, P4Is the mean pressure, Δ P, in the flame tubeoriThe constant beta is the energy conversion efficiency of converting the acoustic energy of the first hole channel with the acoustic throttling function into the kinetic energy for designing the hole pressure drop of the acoustic throttling hole. The constant β is related to the pore diameter d, the pore length 1, with β being larger the smaller d or the larger 1. As can be seen for example from figure 3,
1) designing a pore passage with pressure drop of 3 percent (oil-gas ratio is low, and oscillation combustion is not generated), wherein the pulsating pressure is less than 0.5 percent, and at the moment, acoustic throttling does not occur, so that the actual pressure drop in the combustion chamber is basically the same as the designed pressure drop; when the pulsating pressure is between 0.5 and 3 percent, a small part of the flame tube assembly (such as an inner ring or an outer ring of the flame tube) generates throttling action first, and the pressure drop of the combustion chamber is slightly increased; when the pulsating pressure is more than 3%, most of the flame tube assemblies are throttled, and the pressure drop of a combustion chamber is obviously increased;
2) the design pressure drop of 5% is similar to the 3% case, but due to the design pressure drop increase, it is required that the pulsating pressure exceeds 1%, and a small part of the flame tube assembly is throttled. The staged throttling mode (a small part of the flame tube assembly and then a large part of the flame tube assembly) is related to the opening mode of the cooling holes; additional experimental results designed for 3% and 5% pressure drop also demonstrate that throttling is related to pressure drop.
Based on the principle, the inventor creatively changes the unfavorable phenomenon of the acoustic throttling of the flame tube cooling hole, which is found in a combustion chamber test, into waste (the acoustic throttling of the flame tube cooling hole can reduce the cold effect of the flame tube and is not beneficial to the cooling of the flame tube), and applies the method to the monitoring of the oscillatory combustion, realizes the monitoring of the oscillatory combustion by adopting a static pressure measurement mode, avoids the defect of the attenuation of the dynamic pressure measurement amplitude, also reduces the requirements on a sensor and a data acquisition and control system, reduces the cost of a monitoring device, and also improves the reliability and the service life of the whole monitoring system.
Referring to FIG. 6, in an embodiment, the steps of the method for monitoring oscillating combustion may include:
step A: and collecting the static pressure of air inlet of the flame tube of the combustion chamber and the static pressure in the flame tube.
With reference to fig. 4 and 6, in an embodiment, in step a, the intake static pressure of the combustor liner and the static pressure inside the combustor liner are collected, the static pressure Ps31 of the outer ring cavity 4 of the combustor liner is measured as the intake static pressure of the combustor liner, the static pressure of the outer ring part 6 of the combustor liner is measured as the static pressure Ps4 of the cavity 12 of the combustor liner, and the measured data is collected, but not limited thereto. The static pressure of the ring cavity 10 in the flame tube and the static pressure of the cavity 12 of the flame tube can also be measured, or the static pressure of the air outlet 7 of the diffuser 1 of the combustion chamber or the static pressure of the air inlet of the head 8 of the flame tube and the static pressure of the cavity 12 of the flame tube can also be measured, and the like, and it can be understood that the above collecting positions can be combined to improve the measurement accuracy, but the complexity of the system can be increased. In an embodiment, the static pressure of the air intake of the flame tube of the combustion chamber and the static pressure inside the flame tube can be collected through a signal collection module of the monitoring device, and the collection step specifically includes that a pressure sensor senses the static pressure value and converts the static pressure value into an analog electric signal, and the analog electric signal is converted into a digital signal through an analog/digital converter and is input into an analysis and judgment module of the monitoring device.
And B: obtaining the intake pressure drop of the flame tube according to the intake static pressure of the flame tube and the internal static pressure of the flame tube, comparing the intake pressure drop with a corresponding threshold value, judging whether the intake pressure drop reaches the threshold value, and if so, identifying that the current state is an oscillatory combustion state; and if not, identifying the current state as a stable combustion state.
Specifically, in an embodiment, with reference to fig. 6, according to the collected intake static pressure Ps31 of the flame tube of the combustor flame tube and the static pressure Ps4 inside the flame tube, that is, the collected intake static pressure Ps31 and the static pressure Ps4 of the flame tube are input into the analysis and judgment module, the analysis and judgment module performs low-pass filtering on the digital signal to remove noise; and then, calculating the denoising signal to obtain an intake pressure drop, and comparing the intake pressure drop with a threshold value. The intake pressure drop may be (Ps31-Ps4)/Ps31 (denoted dp)31-4) I.e. outside the flame tubeThe ratio of the static pressure of the ring cavity 4 to the static pressure difference of the liner cavity 12 to the static pressure of the liner outer ring cavity 4 is not limited to this, and the intake pressure drop may also be the ratio of the above difference to the static pressure of the liner cavity 12, or even the above difference itself. The difference value is adopted as the calculated amount of the intake pressure drop, but the reliability is poor, for example, the compressor generates surge, and the difference value can also cause the change of the difference value, so if a reliable result is needed, the difference value is adopted to represent the intake pressure drop, a further optimization algorithm is possibly needed, and the interference of other factors is eliminated. And the ratio is used for representing the intake pressure drop, and the result is more accurate and reliable. Correspondingly, the threshold may be dp31-4Rate of change with time (denoted as D (dp)31-4) The threshold of/Dt), in the embodiment of fig. 6 for determining the outer ring intake pressure drop, that is, in the case where the change rate reaches the upper limit, for example, the outer ring intake pressure drop of the flame tube suddenly increases, the change rate suddenly increases to reach the upper limit, and is identified as oscillatory combustion, and if the change rate does not reach the upper limit, it is identified as stable combustion. The threshold value can also be the outer ring pressure drop dp of the flame tube31-4If the frequency threshold of the oscillatory combustion value is reached, that is, the frequency reaches the upper limit, the oscillatory combustion is identified, and if the frequency does not reach the upper limit, the stable combustion is identified. Of course, the determination and identification may be performed by combining a change rate threshold and a frequency threshold. It is understood that the threshold may be other parameters, and is not limited to the rate of change threshold and the frequency threshold. The change rate threshold, the oscillatory combustion value and the frequency threshold can be used for obtaining the corresponding intake pressure drop change rate, the intake pressure drop value and the frequency data of the oscillatory combustion in the states of various combustion chamber structure parameters and working condition parameters (such as combustion chamber pressure loss parameters and oil-gas ratio) through a combustion chamber test, inputting the data into a database, and calling by an analysis and judgment module of the monitoring device so as to realize quick automatic judgment. The data in the database can be further refined to include thresholds of stable combustion, quasi-stable combustion, oscillatory combustion and strong oscillatory combustion corresponding to various combustion chamber structure parameters and working condition parameters (such as combustion chamber pressure loss parameters and oil-gas ratio) states, and in one embodiment, the analysis and judgment module can detect stable combustion and quasi-stable combustion as shown in fig. 6 when detecting the combustion stateState, and output a safe signal; and detecting signals of the oscillatory combustion and the strong oscillatory combustion output alarm so as to control and intervene combustion of the gas turbine and inhibit the oscillatory combustion.
It can be understood that the threshold value corresponding to the intake pressure drop is not limited to the threshold value corresponding to the intake pressure drop of the outer ring described above. For example, the method may also be a threshold corresponding to the inner ring intake pressure drop, where the inner ring intake pressure drop may be a difference between the static pressure of the inner ring cavity 10 of the flame tube and the static pressure of the cavity 12 of the flame tube, or a ratio of the difference to the static pressure of the inner ring cavity 10 of the flame tube or the static pressure of the cavity 12 of the flame tube; the judgment process is similar to the judgment of the outer ring air inlet pressure drop, when the change rate of the inner ring air inlet pressure drop of the flame tube along with time reaches the upper limit and/or the inner ring air inlet pressure drop of the flame tube reaches the upper limit of the frequency of the oscillatory combustion value, the oscillatory combustion is identified, otherwise, the stable combustion is identified. For example, the threshold corresponding to the head intake pressure drop of the liner may be determined, where the head intake pressure drop may be a difference between the static pressure at the air outlet 7 of the diffuser 1 of the combustion chamber or the static pressure at the air inlet of the liner head 8 and the static pressure in the liner accommodating chamber 12, or a ratio of the difference to the static pressure at the air outlet 7 of the diffuser 1 or the static pressure at the air inlet of the liner head 8 or the static pressure in the liner accommodating chamber 12. As shown in fig. 1 and 2, when the oscillatory combustion occurs, the air flow paths 200 and 300 are closed, and air enters along the air flow path 100, so that the amount of intake air from the liner head 8 increases. However, the judgment process is similar, when the change rate of the head intake pressure drop along with the time reaches the upper limit, and/or the head intake pressure drop reaches the upper limit of the frequency of the oscillatory combustion value, the oscillatory combustion is identified, otherwise, the stable combustion is identified.
It can be understood that the monitoring device corresponding to the embodiment of the monitoring method may be a computer, a server, an intelligent mobile device, a virtual reality device, an augmented reality device, or the like. The monitoring device may include a processor and a computer readable storage medium. The processor may execute instructions stored in a computer-readable storage medium to implement the steps of the monitoring method of comparing the intake pressure drop with a corresponding threshold according to the collected intake pressure drop of the combustor liner, determining whether the intake pressure drop reaches the threshold, identifying the current state as an oscillatory combustion state if the intake pressure drop reaches the threshold, identifying the current state as a stable combustion state if the intake pressure drop does not reach the threshold, and outputting a corresponding oscillatory combustion state signal or a stable combustion signal. In some embodiments, the processor may include at least one hardware processor, such as a microcontroller, microprocessor, Reduced Instruction Set Computer (RISC), Application Specific Integrated Circuit (ASIC), application specific instruction set processor (ASIP), Central Processing Unit (CPU), Graphics Processing Unit (GPU), Physical Processing Unit (PPU), single chip, Digital Signal Processor (DSP), Field Programmable Gate Array (FPGA), advanced reduced instruction set system (ARM), Programmable Logic Device (PLD), any circuit or processor capable of performing at least one function, and the like, or any combination thereof.
A computer-readable storage medium may store computer-readable instructions and/or data. Computer-readable storage media may include memory and storage. The memory may store computer readable instructions and/or data in a volatile manner, for example, may store an analysis determination instruction of the monitoring method, compare the intake pressure drop with a corresponding threshold, determine whether the intake pressure drop reaches the threshold, identify the current state as an oscillatory combustion state if the intake pressure drop reaches the threshold, identify the current state as a stable combustion state if the intake pressure drop does not reach the threshold, and output a corresponding oscillatory combustion state signal or a stable combustion signal. The Memory may be a volatile read-write Memory, such as a Random Access Memory (RAM). The memory may include, for example, Dynamic RAM (DRAM), double data rate synchronous dynamic RAM (DDR SDRAM), Static RAM (SRAM), thyristor RAM (T-RAM), zero capacitance RAM (Z-RAM), and the like.
The memory may store non-volatile computer readable instructions and/or data, for example, may store an analysis determination instruction of a monitoring method, compare the intake pressure drop with a corresponding threshold, determine whether the intake pressure drop reaches the threshold, identify that the current state is an oscillatory combustion state if the intake pressure drop reaches the threshold, identify that the current state is a stable combustion state if the intake pressure drop does not reach the threshold, and output a corresponding oscillatory combustion state signal or a stable combustion signal. The memory may include mass storage, removable storage, Read Only Memory (ROM), etc., or any combination thereof. Exemplary mass storage devices may include magnetic disks, optical disks, solid state drives, and the like. Exemplary removable memory may include flash memory disks, floppy disks, optical disks, memory cards, compact disks, magnetic tape, and the like. Exemplary ROMs may include Mask ROM (MROM), Programmable ROM (PROM), Erasable Programmable ROM (EPROM), Electrically Erasable Programmable ROM (EEPROM), compact disk ROM (CD-ROM), digital versatile disk ROM, and the like. In some embodiments, the memory may be implemented on a cloud platform. By way of example only, the cloud platform may include a private cloud, a public cloud, a hybrid cloud, a distributed cloud, a cross-cloud, a multi-cloud, and the like, or any combination thereof. A computer readable signal medium may comprise a propagated data signal with computer program code embodied therein, for example, on a baseband or as part of a carrier wave. The propagated signal may take any of a variety of forms, including electromagnetic, optical, and the like, or any suitable combination. A computer readable signal medium may be any computer readable medium that is not a computer readable storage medium and that can communicate, propagate, or transport a program for use by or in connection with an instruction execution system, apparatus, or device. Program code on a computer readable signal medium may be propagated over any suitable medium, including radio, electrical cable, fiber optic cable, RF, or the like, or any combination of the preceding.
Computer program code required for the operation of various portions of the present application may be written in any one or more programming languages, including an object oriented programming language such as Java, Scala, Smalltalk, Eiffel, JADE, Emerald, C + +, C #, VB.NET, Python, and the like, a conventional programming language such as C, Visual Basic, Fortran 2003, Perl, COBOL 2002, PHP, ABAP, a dynamic programming language such as Python, Ruby, and Groovy, or other programming languages, and the like. The program code may execute entirely on the user's computer, partly on the user's computer, as a stand-alone software package, partly on the user's computer and partly on a remote computer or entirely on the remote computer or server. In the latter scenario, the remote computer may be connected to the user's computer through any network format, such as a Local Area Network (LAN) or a Wide Area Network (WAN), or the connection may be made to an external computer (for example, through the Internet), or in a cloud computing environment, or as a service, such as a software as a service (SaaS).
For example, the above-mentioned oscillation combustion monitoring device may be integrated into an onboard control unit of the gas turbine, or may be integrated into an external test system, and the external test system may be connected to the combustion chamber or the gas turbine wirelessly or by wire. The monitored oscillatory combustion signals and data can be output to a data display device or a data recording device, so that a gas turbine research and development tester can further improve the engine, or information feedback of the oscillatory combustion is provided for an operator of the gas turbine, so as to help the operator to timely deal with the oscillatory combustion condition. And the control signal can also be output to an onboard control unit of the gas turbine to realize closed-loop control on the oscillatory combustion.
Although the present invention has been described with reference to the present specific embodiments, it will be appreciated by those skilled in the art that the above embodiments are merely illustrative of the present invention, and various equivalent changes and substitutions may be made without departing from the spirit of the invention, and therefore, it is intended that all changes and modifications to the above embodiments within the spirit and scope of the present invention be covered by the appended claims.
Claims (8)
1. A method for monitoring oscillatory combustion of an aircraft engine, comprising
Collecting the static pressure of air inlet of a flame tube of a combustion chamber and the static pressure in the flame tube;
obtaining the intake pressure drop of the flame tube according to the intake static pressure of the flame tube and the internal static pressure of the flame tube, comparing the intake pressure drop with a corresponding threshold value, judging whether the intake pressure drop reaches the threshold value, and if so, identifying that the current state is an oscillation combustion state; if not, identifying the current state as a stable combustion state;
wherein the intake pressure drop of the combustor basket includes one or more of the following values:
the outer ring air inlet pressure drop is the static pressure of the outer ring cavity of the flame tube, and the outer ring air inlet pressure drop is the difference value of the static pressure of the outer ring cavity of the flame tube and the static pressure inside the flame tube, or the ratio of the difference value to the static pressure of the outer ring cavity of the flame tube or the static pressure inside the flame tube;
the inner ring air inlet pressure drop is the static pressure of the inner ring cavity of the flame tube, and the inner ring air inlet pressure drop is the difference between the static pressure of the inner ring cavity of the flame tube and the static pressure inside the flame tube, or the ratio of the difference to the static pressure of the inner ring cavity of the flame tube or the static pressure inside the flame tube;
and the head air inlet pressure drop is the static pressure of the diffuser air outlet of the combustion chamber or the static pressure of the flame tube head air inlet, and the head air inlet pressure drop is the difference value of the static pressure of the diffuser air outlet of the combustion chamber or the static pressure of the flame tube head air inlet and the static pressure in the flame tube, or the ratio of the difference value to the static pressure of the diffuser air outlet or the static pressure of the flame tube head air inlet or the static pressure in the flame tube.
2. The monitoring method according to claim 1, wherein the threshold value includes a threshold value of a rate of change of the intake pressure drop with time and/or a threshold value of the number of times the intake pressure drop reaches a value of oscillatory combustion, which is a value of intake pressure drop at which oscillatory combustion occurs according to a structure of a combustion chamber and a condition.
3. A computer readable storage medium for an aircraft engine having computer instructions stored thereon, wherein the instructions, when executed by a processor, perform the steps of the monitoring method according to claim 1 or 2, which are computer-executable.
4. A monitoring device for oscillatory combustion of an aircraft engine, characterized in that it comprises a processor and a computer-readable storage medium according to claim 3.
5. A monitoring device for oscillatory combustion of an aeroengine, characterized by the fact of carrying out a monitoring method according to claim 1 or 2, comprising:
the signal acquisition module at least acquires intake static pressure of a flame tube of the combustion chamber and internal static pressure of the flame tube;
the analysis and judgment module is used for obtaining the intake pressure drop of the flame tube according to the intake static pressure and the static pressure in the flame tube, comparing the intake pressure drop with a corresponding threshold value, judging whether the intake pressure drop reaches the threshold value, and if so, identifying the current state as the oscillation combustion state; and if not, identifying the current state as a stable combustion state.
6. The monitoring device of claim 5, wherein the signal acquisition module comprises a pressure sensor for sensing a static pressure value and converting the static pressure value into an analog electrical signal, and an analog/digital converter for converting the analog electrical signal into a digital signal, and the digital signal is output to the analysis and judgment module.
7. The monitoring device of claim 5, wherein the monitoring device comprises a database storing a plurality of threshold values corresponding to a plurality of combustion chamber configurations and operating conditions for which oscillatory combustion occurs, and the analysis and determination module retrieves the threshold values for comparison of the intake air pressure drop with the corresponding threshold values.
8. A gas turbine engine, wherein the gas turbine engine is an aircraft engine, comprising a monitoring device for oscillatory combustion according to any one of claims 5 to 7.
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