CN115324742A - Self-adaptively adjusted boosting oil supply control method and device for turbofan engine - Google Patents
Self-adaptively adjusted boosting oil supply control method and device for turbofan engine Download PDFInfo
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- CN115324742A CN115324742A CN202210969358.XA CN202210969358A CN115324742A CN 115324742 A CN115324742 A CN 115324742A CN 202210969358 A CN202210969358 A CN 202210969358A CN 115324742 A CN115324742 A CN 115324742A
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/22—Fuel supply systems
Abstract
The application belongs to the technical field of engine tests, and particularly relates to a thrust augmentation oil supply control method and device for self-adaptive adjustment of a turbofan engine. The method comprises the step S1 of designing the oil quantity W according to the oil supply rule of a stress application I area of a specified working point A fa1 The oil supply is carried out by the first set multiple, and timing is started; s2, determining whether a stress application connection condition is met, and if the stress application connection condition is met, controlling the linear transition of the oil quantity of a stress application I area to the designed oil quantity W within a first set time period fa1 If the timing time reaches the forced oil supply time of the stress application culvert and the stress application connection condition is not met, the oil quantity of the stress application I area is controlled to be linearly transited to the designed oil quantity W in the second set time period fa1 And (3) a third set multiple. This application has promoted afterburning switch-on reliability, has promoted afterburning switch-on process job stabilization nature simultaneously.
Description
Technical Field
The application belongs to the technical field of engine control, and particularly relates to a thrust augmentation oil supply control method and device for self-adaptive adjustment of a turbofan engine.
Background
The boosting turbofan engine is the first choice of the power device of the military fighter plane in the society at present. By controlling the afterburning oil supply rule, the afterburner can be reliably communicated and stably work, the speed of the air flow at the outlet of the engine spray pipe is increased, the thrust is greatly increased, and the maneuvering performance of the airplane is improved.
The reliable connection of the afterburner is a premise of ensuring the reliable work of afterburner, is one of the design difficulties of afterburner, and particularly under the condition of high altitude and left boundary, the fuel atomization effect, the flame propagation capacity and the reliable connection of lean and rich oil-gas ratio are greatly reduced due to the reduction of the ambient temperature and pressure, and the low altitude state causes the difficulty of connecting afterburner.
Afterburning room generally adopts the mode of subregion control fuel feeding, and the design of afterburning I district's fuel feeding law is the key of deciding afterburning turn-on ability, through carrying out optimization adjustment to afterburning I district's fuel feeding law, can promote afterburning room's turn-on ability, afterburning I district's fuel feeding law that currently generally adopts mainly has two kinds: firstly, a designed state oil supply plan is adopted in the whole process, the oil supply quantity is only related to the state parameters of the engine host, the adaptive adjustment is not carried out along with the stress application connection condition, and the oil quantity in the designed state is used for connection, ignition, flame connection and transmission with each stress application area and the like; and secondly, adopting a progressive oil supply plan, regulating the oil supply plan at the early stage of oil supply, mainly igniting, and after delaying for a fixed time, regulating the oil supply plan to a designed or higher state to stably work.
The conventional afterburner I-area fuel supply rule can basically perform normal connection control on an afterburner, but has the following defects:
1. the first method is unreliable in forced connection under the condition of high altitude left boundary. The method uses a designed state oil supply plan in the whole course, the normal connection control of an afterburner can be basically ensured due to the fact that the oil-gas ratio range is large when the afterburner is connected under the low-altitude condition, but under the condition of a high-altitude left boundary, particularly in the acceleration process of a main engine, the bypass ratio is reduced, the air flow of a stress ignition area in a culvert flow passage is reduced, rich oil combustion is easily caused by using the designed oil quantity, and in addition, the oil supply precision deviation, the fuel oil atomization effect deviation, the main engine state matching deviation and other factors easily cause the oil-gas ratio to be improper when the afterburner is connected, so that the connection reliability is influenced.
2. And the second method reduces the anti-interference capability of the afterburner under the condition of high altitude left boundary. The method II uses an oil supply plan passive control method adjusted according to time, an oil supply plan lower than a designed oil amount is used for ignition, the designed oil amount works stably, boost connection is facilitated in principle, but in order to improve ignition reliability, the duration time lower than the oil supply plan in a designed state needs to be prolonged as far as possible, the stability of flame connection of each boost region is ignored, particularly, after boost connotation and outer culvert oil supply flame connection are successful, the nozzle opening area is passively followed with the amplification moment, the inlet state of a boost combustion chamber is reduced, the oil amount of a boost region I is still at a lower level, the anti-interference capability of the boost combustion chamber is reduced, and the boost working stability is influenced.
Disclosure of Invention
In order to solve one of the problems, the application provides a thrust augmentation fuel supply control method and a thrust augmentation fuel supply control device for self-adaptive adjustment of a turbofan engine.
The application provides a thrust augmentation fuel supply control method of turbofan engine self-adaptive adjustment in a first aspect, and the method mainly comprises the following steps:
step S1, designing oil quantity W according to oil supply rule of stress application I area of specified working point A fa1 The oil supply is carried out by the first set multiple, and timing is started;
s2, determining whether a stress application connection condition is met, and if the stress application connection condition is met, controlling the linear transition of the oil quantity of a stress application I area to the designed oil quantity W within a first set time period fa1 If the timing time reaches the forced oil supply time of the stress application culvert and the stress application connection condition is not met, the oil quantity of the stress application I area is controlled to be linearly transited to the designed oil quantity W in the second set time period fa1 And (3) a third set multiple.
Preferably, the step S1 further includes determining a first setting multiple, the determining the first setting multiple includes:
obtaining the oil quantity W designed according to the oil supply rule of a stress application I area under the condition of a specified working point A determined by part simulation analysis and part test fa1 And a lean-rich boundary;
calculating lean boundary relative to design oil mass W fa1 Ratio k of Lean oil And rich boundary relative to design oil mass W fa1 Ratio k of Rich oil ；
Determining the first setting multiple, the first setting multiple being taken from k Lean oil Any value between-1.
Preferably, the step S2 of determining whether the engine satisfies the boost-on condition includes:
the signal of detecting the flame given by the afterburner flame detector and the duration of which reaches a specified value, the specified value being taken from 0s to 0.3s.
Preferably, the step S2 of determining whether the engine satisfies the boost on condition includes:
calculating the difference value between the turbine rear pressure at the current moment and the turbine rear pressure at the moment when the throttle lever enters the stress application domain;
if the difference value is larger than the set value and the duration reaches the specified value, the specified value is taken from 0s to 0.3s, and the set value is delta P 6 ×k Is connected to Wherein, Δ P 6 For the amount of change in the turbine rear pressure, k, at lean boundary switch-on in the boost I region Is connected through The value range is 0.5-1.0.
Preferably, determining the amount of change in the pressure after the turbine at which the boost i region is switched on at the lean boundary includes:
at a designated working point A, calculating the area of a first nozzle of the engine in an intermediate state by using a complete machine performance simulation model;
calculating the first turbine rear pressure when the oil supply quantity of an afterburner reaches the lean boundary oil quantity in an afterburning state;
adjusting the nozzle area of the engine in the intermediate state, and calculating the second turbine rear pressure when the oil supply quantity of the afterburner reaches the lean oil boundary oil quantity and the nozzle area is equal to the first nozzle area in the afterburner state;
and determining the change amount of the pressure after the turbine when the boost I area is connected at the lean oil boundary according to the difference value of the pressure after the second turbine and the pressure after the first turbine.
The application second aspect provides a afterburning fuel feeding controlling means of turbofan engine self-adaptation regulation, mainly includes:
an initial oil supply control module for designing oil quantity W according to the oil supply rule of the stress application I area of the designated working point A fa1 The oil supply is carried out by the first set multiple, and timing is started;
the stress application connection oil supply control module is used for determining whether stress application connection conditions are met or not, and controlling the linear transition of the oil quantity of a stress application I area to the designed oil quantity W within a first set time period if the stress application connection conditions are met fa1 If the timing time reaches the forced oil supply time of the stress application culvert and the stress application connection condition is not met, the oil quantity of the stress application I area is controlled to be linearly transited to the designed oil quantity W in the second set time period fa1 And (3) a third set multiple.
Preferably, the initial fuel supply control module includes:
a boundary determining unit for obtaining the oil quantity W designed by the oil supply rule of the stress application I area under the condition of the specified working point A determined by the simulation analysis of the component and the test of the component fa1 And a lean-rich boundary;
a proportion calculation unit for calculating the lean boundary relative to the design oil amount W fa1 Ratio k of Lean oil And rich boundary relative to design oil mass W fa1 Ratio k of Rich in oil ；
A first setting multiple calculation unit for determining the first setting multiple, the first setting multiple being taken from k Lean oil Any value between-1.
Preferably, the boost-on fuel supply control module comprises a first boost-on condition determination unit for determining that boost-on regulation is satisfied after a signal for detecting flame is given by a flame detector of the boost combustor and the duration time reaches a specified value, wherein the specified value is taken from 0s to 0.3s.
Preferably, the boost connection oil supply control module comprises a second boost connection condition determining unit, which is used for calculating the difference value between the turbine rear pressure at the current moment and the turbine rear pressure at the moment when the throttle lever enters the boost domain; if the difference is larger than a set value and the duration time reaches a specified value, the judgment that the stress application connection adjustment is met is given, the specified value is taken from 0s to 0.3s, and the set value is delta P 6 ×k Is connected to Wherein, Δ P 6 For the change of pressure after turbine, k, at lean boundary switch-on in boost I region Is connected through The value range is 0.5-1.0.
Preferably, the second energization-on condition determination unit includes:
the intermediate state nozzle area determining unit is used for calculating the first nozzle area of the engine in the intermediate state by using a complete machine performance simulation model at a designated working point A;
a first turbine rear pressure determining unit for calculating a first turbine rear pressure at which an afterburner fuel supply amount reaches a lean boundary fuel amount in an afterburner state;
the second turbine rear pressure determining unit is used for adjusting the nozzle area of the engine in the middle state, and calculating the second turbine rear pressure when the oil supply quantity of the afterburner reaches the lean oil boundary oil quantity and the nozzle area is equal to the first nozzle area in the afterburner state;
and the post-turbine pressure variation calculating unit is used for determining the post-turbine pressure variation of the stress application I area when the lean boundary is connected according to the difference value of the second post-turbine pressure and the first post-turbine pressure.
This application has promoted afterburning switch-on reliability, has promoted afterburning switch-on process job stabilization nature simultaneously.
Drawings
Fig. 1 is a flowchart of a preferred embodiment of a self-adaptive boost oil supply control method for a turbofan engine according to the present application.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are implementations that are part of this application and not all implementations. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application, and should not be construed as limiting the present application. All other embodiments obtained by a person of ordinary skill in the art without any inventive work based on the embodiments in the present application are within the scope of protection of the present application. Embodiments of the present application will be described in detail below with reference to the drawings.
Firstly, a flight envelope is introduced, the flight envelope is one of a plurality of indexes for comprehensively evaluating the flight performance of an airplane and is composed of a very simple two-dimensional curve, the abscissa is the flight speed, the ordinate is the flight altitude, the left boundary line of the flight envelope refers to the minimum speed of the airplane at any altitude, the speed value is completely determined by the overall aerodynamic characteristics of the airplane, in general, the minimum speed value of the airplane capable of keeping horizontal flight at a certain altitude is also referred to, and once the speed is lower than the minimum speed value, the airplane enters a stall state, and the lift force generated on the wings of the airplane is smaller than the weight of the airplane. In contrast, the right boundary is the highest velocity value that can be achieved for full force acceleration of this type of aircraft at a certain altitude. The magnitude of this speed depends on the thrust of the engine and the aerodynamic characteristics of the aircraft itself, and when the speed reaches a maximum, the maximum thrust output by the aircraft engine is exactly equal to the aerodynamic drag of the aircraft at the speed which the aircraft cannot exceed.
The purpose of this application is just in the left boundary condition of flight envelope, carries out the design of afterburning I district's oil supply law.
The application provides a thrust augmentation fuel supply control method of turbofan engine self-adaptive adjustment, as shown in fig. 1, mainly including:
step S1, according toOil quantity W designed according to oil supply rule of stress application I area of specified working point A fa1 And the oil supply is performed at the first set multiple of (1) and the timing is started.
Specifically, when the oil supply condition of the stress application I area is satisfied, the oil supply is carried out according to W fa1 ×k Initial Initial oil supply is performed and timing is started at the same time.
In some alternative embodiments, step S1 further comprises determining a first set multiple, i.e. the parameter k above Initial Determining the first set multiple comprises:
obtaining the oil quantity W designed according to the oil supply rule of a stress application I area under the condition of a specified working point A determined by part simulation analysis and part test fa1 And a lean-rich boundary;
calculating lean boundary relative to design oil mass W fa1 Ratio k of Lean oil And rich boundary relative to design oil mass W fa1 Ratio k of Rich in oil ；
Determining the first setting multiple, the first setting multiple being taken from k Lean oil Any value between-1. I.e. initial oil supply coefficient k Initiation of Recommended value range k Lean oil ～1。
In the embodiment, the working point A recommends selecting the height range from 12km to 16km and the speed range from 300km/h to 600km/h, and adaptively adjusting according to the working envelope of the engine.
S2, determining whether a stress application connection condition is met, and if the stress application connection condition is met, controlling the linear transition of the oil quantity of a stress application I area to the designed oil quantity W within a first set time period fa1 If the timing time reaches the forced oil supply time of the stress application culvert and the stress application connection condition is not met, the oil quantity of the stress application I area is controlled to be linearly transited to the designed oil quantity W in the second set time period fa1 And (3) a third set multiple.
In this embodiment, the first set time period is C, the value range of C is 0.5s to 3s, the second set time period is E, and the value range of E is 2s to 5s.
Second set multiple k Stabilization 1 And a third set multiple k Stabilization 2 All take values from 1 to k Rich oil 。
For example, when the stress switch-on condition is satisfied, the oil quantity in the I region of the controlled stress is linearly transited to W within 1s fa1 ×k Stabilization 1 (ii) a When the timing time is satisfied, the forced oil supply time of the stress application culvert is reached, and the stress application connection condition is not satisfied all the time, the oil quantity in the stress application I area is controlled to be linearly transited to W within 4s fa1 ×k Stabilization 2 。
In some alternative embodiments, the step S2 of determining whether the engine satisfies an boost on condition includes: a signal of detection of the flame given by the afterburner flame detector and the duration of time reaching a specified value, said specified value being taken from 0s to 0.3s. In an alternative embodiment, determining whether the engine satisfies the boost-on condition may further include: calculating the turbine rear pressure P at the current moment 6 Turbine rear pressure P corresponding to the moment when the throttle lever enters the stress application domain 6 initial A difference of (d); if the difference is larger than the set value, and the duration time reaches the specified value.
The predetermined value is any one value from 0s to 0.3s, and the set value is Δ P 6 ×k Is connected to Wherein, Δ P 6 For the amount of change in the turbine rear pressure, k, at lean boundary switch-on in the boost I region Is connected to The value range is any value from 0.5 to 1.0.
In some alternative embodiments, the amount of change in pressure Δ P after the turbine is determined when the boost region I is switched on at the lean boundary 6 The method comprises the following steps:
at a designated working point A, calculating the first nozzle area A of the engine in an intermediate state by using a complete machine performance simulation model 8 Standard ；
Calculating a first turbine aft pressure P at which an afterburner fuel charge reaches a lean boundary fuel charge under an afterburner condition 6 Standard ；
Adjusting the nozzle area of the engine in the intermediate state, calculating the oil supply quantity of the afterburner reaching the lean oil boundary oil quantity in the afterburner state, wherein the nozzle area is equal to the first nozzle area A 8 Standard Equal second turbine aft pressure P 6 is connected ；
From the second turbine rear pressure to the first turbine rear pressureThe difference between the values of (A) and (B) determines the amount of change in the pressure after the turbine Δ P when the boost region I is connected at the lean boundary 6 ＝P 6 is connected -P 6 Standard 。
The present application has the following advantages.
1. And the stress application connection reliability is improved. In the transition process, the bypass ratio of the engine is reduced, the air flow of the stress application ignition area located in the inner bypass is reduced, the required fuel flow is also reduced, the fuel quantity lower than the designed oil quantity is used for switching on control, the problem of rich oil ignition in the first method is solved, and the stress application switching reliability is improved.
2. The working stability of the stress application connection process is improved. The afterburner comprises a first afterburner body, a second afterburner body, a third afterburner body, a fourth afterburner body and a fourth afterburner body, wherein the third afterburner body is connected with the fourth afterburner body through a connecting piece, the fourth afterburner body is connected with the fourth afterburner body through a connecting piece, and the fourth afterburner body is connected with the fourth afterburner body through a connecting piece.
The second aspect of the present application provides a self-adaptive turbofan engine thrust augmentation fuel supply control apparatus corresponding to the above method, which mainly includes:
an initial oil supply control module for designing oil quantity W according to the oil supply rule of the stress application I area of the designated working point A fa1 The oil supply is carried out by the first set multiple, and timing is started;
the stress application connection oil supply control module is used for determining whether stress application connection conditions are met or not, and controlling the linear transition of the oil quantity of a stress application I area to the designed oil quantity W within a first set time period if the stress application connection conditions are met fa1 If the timing time reaches the forced oil supply time of the stress application culvert and the stress application connection condition is not met, the oil quantity of the stress application I area is controlled to be linearly transited to the designed oil quantity W in the second set time period fa1 And (3) a third set multiple.
In some optional embodiments, the initial fueling control module comprises:
a boundary determining unit for obtaining the oil quantity W designed by the oil supply rule of the stress application I area under the condition of the specified working point A determined by the simulation analysis of the component and the test of the component fa1 And lean and rich sidesA boundary;
a proportion calculation unit for calculating the lean boundary relative to the design oil amount W fa1 Ratio k of Lean oil And the rich boundary is relative to the design oil mass W fa1 Ratio k of Rich oil ；
A first setting multiple calculation unit for determining the first setting multiple, the first setting multiple being taken from k Lean oil Any value between-1.
In some optional embodiments, the boost-on fuel supply control module comprises a first boost-on condition determination unit for determining that boost-on regulation is satisfied after a signal of flame detection is given by a boost combustor flame detector and a duration reaches a prescribed value, the prescribed value being taken from 0s to 0.3s.
In some alternative embodiments, the boost-on fueling control module includes a second boost-on condition determination unit configured to calculate a difference between the turbine rear pressure at the present time and the turbine rear pressure at the time when the throttle lever enters the boost region; if the difference value is larger than the set value and the duration reaches a specified value, the judgment that the stress application connection adjustment is met is given, the specified value is taken from 0s to 0.3s, and the set value is delta P 6 ×k Is connected to Wherein, Δ P 6 For the amount of change in the turbine rear pressure, k, at lean boundary switch-on in the boost I region Is connected to The value range is 0.5-1.0.
In some alternative embodiments, the second energization-on-condition determining unit includes:
the intermediate state nozzle area determining unit is used for calculating the first nozzle area of the engine in an intermediate state by using a complete machine performance simulation model at a designated working point A;
a first turbine rear pressure determining unit for calculating a first turbine rear pressure at which an afterburner fuel supply amount reaches a lean boundary fuel amount in an afterburner state;
the second turbine rear pressure determining unit is used for adjusting the nozzle area of the engine in the middle state, and calculating the second turbine rear pressure when the oil supply quantity of the afterburner reaches the lean oil boundary oil quantity and the nozzle area is equal to the first nozzle area in the afterburner state;
and the post-turbine pressure variation calculating unit is used for determining the post-turbine pressure variation of the stress application I area when the lean boundary is connected according to the difference value of the second post-turbine pressure and the first post-turbine pressure.
Although the present application has been described in detail with respect to specific embodiments and general description, it will be apparent to those skilled in the art that some modifications or improvements may be made based on the present application. Accordingly, such modifications and improvements are intended to be within the scope of this invention as claimed.
Claims (10)
1. A self-adaptive regulation boosting oil supply control method of a turbofan engine is characterized by comprising the following steps:
step S1, designing oil quantity W according to oil supply rule of stress application I area of specified working point A fa1 The oil supply is carried out by the first set multiple, and timing is started;
s2, determining whether a stress application connection condition is met, and if the stress application connection condition is met, controlling the linear transition of the oil quantity of a stress application I area to the designed oil quantity W within a first set time period fa1 If the timing time reaches the forced oil supply time of the stress application culvert and the stress application connection condition is not met, the oil quantity of the stress application I area is controlled to be linearly transited to the designed oil quantity W in the second set time period fa1 And (3) a third set multiple.
2. The self-adaptive turbofan engine fuel supply control method of claim 1 wherein step S1 further comprises determining a first set multiple, the determining the first set multiple comprising:
obtaining the oil quantity W designed according to the oil supply rule of a stress application I area under the condition of a specified working point A determined by part simulation analysis and part test fa1 And a lean-rich boundary;
calculating a lean boundary with respect to a design fuel quantity W fa1 Ratio k of Lean oil And rich boundary relative to design oil mass W fa1 Ratio k of Rich oil ；
Determining the first setting multiple, the first setting multiple being taken from k Lean oil Any value between-1.
3. The self-adaptive turbofan engine thrust augmentation fuel supply control method of claim 1 wherein the step S2 of determining whether the engine satisfies thrust augmentation key-on conditions comprises:
the signal of detecting the flame given by the afterburner flame detector and the duration of which reaches a specified value, the specified value being taken from 0s to 0.3s.
4. The self-adaptive turbofan engine thrust augmentation fuel supply control method of claim 1 wherein the step S2 of determining whether the engine satisfies thrust augmentation key-on conditions comprises:
calculating the difference value between the turbine rear pressure at the current moment and the turbine rear pressure at the moment when the throttle lever enters the stress application domain;
if the difference is greater than the set value and the duration reaches the specified value, the specified value is taken from 0s to 0.3s, and the set value is delta P 6 ×k Is connected to Wherein, Δ P 6 For the amount of change in the turbine rear pressure, k, at lean boundary switch-on in the boost I region Is connected through The value range is 0.5-1.0.
5. The self-adaptive turbofan engine thrust augmentation fuel supply control method of claim 4 wherein determining the amount of change in the turbine rear pressure at which the thrust augmentation i region is turned on at the lean boundary comprises:
at a designated working point A, calculating the area of a first nozzle of the engine in an intermediate state by using a complete machine performance simulation model;
calculating a first turbine rear pressure when the afterburner oil supply reaches a lean boundary oil amount under an afterburner state;
adjusting the nozzle area of the engine in the intermediate state, and calculating the second turbine rear pressure when the oil supply quantity of the afterburner reaches the lean oil boundary oil quantity and the nozzle area is equal to the first nozzle area in the afterburner state;
and determining the change amount of the pressure after the turbine when the boost I area is connected at the lean oil boundary according to the difference value of the pressure after the second turbine and the pressure after the first turbine.
6. The utility model provides a thrust augmentation fuel feeding control device of turbofan engine self-adaptation adjustment which characterized in that includes:
an initial oil supply control module for designing oil quantity W according to the oil supply rule of the stress application I area of the designated working point A fa1 The oil supply is carried out by the first set multiple, and timing is started;
the stress application connection oil supply control module is used for determining whether stress application connection conditions are met or not, and controlling the linear transition of the oil quantity of a stress application I area to the designed oil quantity W within a first set time period if the stress application connection conditions are met fa1 If the forced oil supply condition is not met after the timing time reaches the forced oil supply time of the forced bypass, the oil quantity of the forced I area is controlled to linearly transit to the designed oil quantity W within a second set time period fa1 And (3) a third set multiple.
7. The self-adaptive turbofan engine thrust augmentation fuel supply control apparatus of claim 6 wherein the initial fuel supply control module comprises:
a boundary determining unit for obtaining the oil quantity W designed by the oil supply rule of the stress application I area under the condition of the specified working point A determined by the simulation analysis of the component and the test of the component fa1 And a lean-rich boundary;
a proportion calculation unit for calculating the lean boundary relative to the design oil amount W fa1 Ratio k of Lean oil And rich boundary relative to design oil mass W fa1 Ratio k of Rich oil ；
A first setting multiple calculation unit for determining the first setting multiple, the first setting multiple being taken from k Lean oil Any value between-1.
8. The turbofan engine adaptive adjustment augmented fuel supply control apparatus according to claim 6 wherein the augmented fuel supply control module comprises a first augmented fuel supply condition determining unit for determining that augmented fuel supply adjustment is satisfied after a duration time reaches a prescribed value given by an augmented combustor flame detector, the prescribed value being taken from 0s to 0.3s.
9. The self-adaptively adjusted boost oil supply control device of the turbofan engine according to claim 6, wherein the boost connection oil supply control module comprises a second boost connection condition determination unit for calculating a difference between a turbine rear pressure at a current time and a turbine rear pressure at a time when the throttle lever enters a boost region; if the difference is larger than a set value and the duration time reaches a specified value, the judgment that the stress application connection adjustment is met is given, the specified value is taken from 0s to 0.3s, and the set value is delta P 6 ×k Is connected to Wherein, Δ P 6 For the amount of change in the turbine rear pressure, k, at lean boundary switch-on in the boost I region Is connected to The value range is 0.5-1.0.
10. The self-adaptive turbofan engine fuel supply control apparatus of claim 9 wherein the second boost connection condition determining unit comprises:
the intermediate state nozzle area determining unit is used for calculating the first nozzle area of the engine in the intermediate state by using a complete machine performance simulation model at a designated working point A;
a first turbine rear pressure determining unit for calculating a first turbine rear pressure at which an afterburner fuel supply amount reaches a lean boundary fuel amount in an afterburner state;
the second turbine rear pressure determining unit is used for adjusting the nozzle area of the engine in the middle state, and calculating the second turbine rear pressure when the oil supply quantity of the afterburner reaches the lean oil boundary oil quantity and the nozzle area is equal to the first nozzle area in the afterburner state;
and the post-turbine pressure variation calculating unit is used for determining the post-turbine pressure variation of the stress application I area when the lean boundary is connected according to the difference value of the second post-turbine pressure and the first post-turbine pressure.
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115875138A (en) * | 2023-02-06 | 2023-03-31 | 中国航发沈阳发动机研究所 | Method and device for controlling aviation gas turbine engine in different domains and different time |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115875138A (en) * | 2023-02-06 | 2023-03-31 | 中国航发沈阳发动机研究所 | Method and device for controlling aviation gas turbine engine in different domains and different time |
| CN115875138B (en) * | 2023-02-06 | 2023-05-16 | 中国航发沈阳发动机研究所 | Domain and time division control method and device for aviation gas turbine engine |
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