阅读说明：本技术 调节包括临时功率增加装置的涡轮机的方法 (Method for regulating a turbomachine comprising a temporary power augmentation device ) 是由 F·G·普赛 B·Y·G·莫因 于 2020-04-10 设计创作，主要内容包括：用于调节包括临时功率增加装置(26)的涡轮机(10)的方法,所述调节方法包括步骤(E3),在该步骤中,根据以下调节注射的制冷流体流率,即大气压力(P0)和/或环境温度(T0)和/或诸如气体发生器的转速(N1)、低压涡轮或自由涡轮的转速(N2)、在压缩机级的出口处的气体压力(P3)、在低压涡轮或自由涡轮的入口处的温度(T45)、驱动扭矩(TQ)中的至少一个参数和/或直升机转子的总距(XPC)或涡轮螺旋桨发动机的螺距。(Method for regulating a turbomachine (10) comprising a temporary power augmentation device (26), said regulation method comprising a step (E3) in which the injected refrigerating fluid flow rate is regulated as a function of at least one parameter selected from among atmospheric pressure (P0) and/or ambient temperature (T0) and/or rotational speed (N1) such as of a gas generator, rotational speed (N2) of a low-pressure turbine or free turbine, gas pressure (P3) at the outlet of a compressor stage, temperature (T45) at the inlet of a low-pressure turbine or free turbine, drive Torque (TQ) and/or total pitch (XPC) of a helicopter rotor or pitch of a turboprop.)

1. A method of controlling a turbine (10), the turbine (10) being configured to be assembled on an aircraft (100), the turbine (10) comprising a temporary power augmentation device (26), the device comprising a reservoir (26A) and an injection circuit (26B), the reservoir (26A) being configured to contain a coolant, the injection circuit (26B) being configured to inject the coolant via an injection manifold (26B3) upstream of at least one compressor stage (12, 14) of the turbine (10), an injection flow rate of the coolant being variable, the control method comprising: a step (E2) of activating the temporary power increase device (26), in which a coolant is injected upstream of at least one compressor stage (12, 14) of the turbine (10); and a step (E3) of controlling the flow rate of the coolant, wherein the flow rate of the injected refrigerant is adjusted as a function of the atmospheric pressure (P0), and/or of the ambient temperature (T0), and/or of at least one parameter of the turbine such as the rotational speed of the gas generator (N1), of the low-pressure turbine or of the power turbine (N2), of the gas pressure at the outlet of the compressor stage (P3), of the temperature at the inlet of the low-pressure turbine or of the power turbine (T45), of the engine Torque (TQ), and/or of at least one parameter of the aircraft (100) for which the turbine (10) is configured to be assembled such as the total pitch of the helicopter rotor (XPC) or of the propellers of one or more turboprop engines.

2. Method according to claim 1, characterized in that the flow rate of the injected coolant is adjusted such that the coolant/air mass ratio is between 0.5% and 15%, such as between 1% and 12%.

3. Method according to claim 1 or 2, characterized in that the flow rate of the injected coolant is regulated as a function of at least one other parameter among the temperature (Tf) of the coolant from inside the reservoir and the pressure (Pf) of the coolant at the level of the injection manifold.

4. A method according to any one of claims 1-3, characterized in that the temporary power increase means (26) are activated if a momentary power loss of the turbine (10) is detected and/or if it is detected that the turbine (10) goes into a predetermined rated power and/or if an additional power demand and/or user demand is detected.

5. Method according to claim 4, characterized in that the temporary power increase means (26) are activated according to:

-at least one parameter of the turbomachine, such as the rotational speed of the gas generator (N1), the rotational speed of the low-pressure turbine or power turbine (N2), the gas pressure at the outlet of the compressor stage (P3), the temperature at the inlet of the low-pressure turbine or power turbine (T45), the engine Torque (TQ), and/or

-at least one parameter of the aircraft (100), wherein the turbine (10) is configured to be assembled such as the collective pitch (XPC) of helicopter rotors or the pitch of one or more turboprop engines.

6. The method according to any of claims 1 to 5, characterized by determining whether the temporary power increasing means (26) is activatable before activating (E1) the temporary power increasing means (26).

7. The method of claim 6, wherein: determining whether the temporary power increasing means (26) is activatable as a function of at least one parameter from among a level of coolant (Nf) inside the reservoir, a temperature of coolant (Tf) inside the reservoir, a pressure of coolant (Pf) at the level of the injection manifold, and a rotational speed (Nep) of an electric pump of an injection circuit of the temporary power increasing means.

8. Method according to any one of claims 1 to 7, characterized in that the activation of the temporary power increase means (26) is stopped (E4) as a function of at least one parameter from among the level of coolant (Nf) inside the reservoir, the temperature of the coolant inside the reservoir (Tf), the activation time of the temporary power increase means, the instantaneous power of the turbine, or a user request.

9. A computer program comprising instructions for carrying out the method according to any one of claims 1 to 8 when said computer program is executed by a computer.

10. A recording medium (30A) readable by a computer, having recorded thereon the computer program of claim 9.

11. An integrated circuit or electronic card configured for performing the method of any one of claims 1 to 8.

Technical Field

The present disclosure relates to a method of controlling a turbine comprising a temporary power augmentation device.

The term "turbine" refers to any aircraft (craft) with a gas turbine generating power, which may include in particular a turbojet engine supplying the thrust required for propulsion through reaction to the high-speed hot exhaust gases, and a turbine shaft supplying the power through rotation of the engine shaft. For example, turbine shafts are used as engines for helicopters, ships, trains, or as industrial engines. Turboprop engines (turbine shafts driving propellers) are also turbine shafts used as aircraft engines.

Background

Different devices are known for temporarily increasing the power of a turbine, for example FR 3000137 or FR 3057614. Such a device is used to inject a coolant upstream of the compressor of the turbine, which has the effect of temporarily increasing its power.

However, these known devices consume a large amount of coolant, which poses a problem in view of the fact that the coolant must be carried on the aircraft, which limits its usability. Furthermore, the injection is not optimized throughout the enclosure. Thus, there is a need in the art.

Disclosure of Invention

One embodiment relates to a method of controlling a turbomachine comprising a temporary power augmentation device, the device comprising a reservoir configured to contain a coolant and an injection circuit configured to inject the coolant via an injection manifold upstream of at least one compressor stage of the turbomachine, the injection flow rate of the coolant being variable, the control method comprising: a step of activating a temporary power augmentation device, in which a coolant is injected upstream of at least one compressor stage of the turbomachine; and a step of controlling the flow rate of the coolant, wherein the flow rate of the injected refrigerant, i.e., atmospheric pressure, is adjusted according to; and/or ambient temperature; and/or at least one parameter of the turbine such as the rotational speed of the gas generator, the rotational speed of the low-pressure turbine or of the power turbine, the gas pressure at the outlet of the compressor stage, the temperature at the inlet of the low-pressure turbine or of the power turbine, the engine torque; and/or the turbine is configured as at least one parameter of the aircraft to be assembled, such as the collective pitch of the helicopter rotors (collective pitch) or the pitch of the propellers of one or more turboprop engines.

In this context, the terms "downstream" and "upstream" are considered along the normal flow direction of the gases inside the turbine.

For example, the coolant may be water or a mixture of water and an additive such as an antifreeze agent, such as methanol, ethanol, or ethylene glycol. Hereinafter, the term "coolant" is to be understood as "cooling fluid" unless otherwise indicated.

For example, the injection flow rate may be variable due to a variable flow pump, such as a pump having a fixed displacement but a variable speed rotor or a pump having a fixed speed rotor but a variable displacement. In such an example, a pump may be used to pump coolant from the reservoir and inject it at a predetermined pressure via the manifold, in which case the coolant reservoir need not be pressurized. According to another example, the injection flow rate may be variable due to a variable opening valve. In such an example, the reservoir may be pressurized. According to yet another example, the injection circuit comprises a pump and a valve, the flow rate of the pump and/or the opening of the valve being variable.

Such a method is applicable to any type of aircraft in which the turbine is configured to be assembled (e.g. fixed or rotating wing, presence of one or more turbines, etc.).

The inventors have found that when the flow rate of the injected coolant is adjusted according to atmospheric pressure or ambient temperature or both, the flow rate of the injected coolant can be as close as possible to the actual requirement of the turbine for a given pressure increase. For example, the requirements for such coolant injection may be limited to a low height and high temperature envelope. E.g., from ISA to ISA +30 and from 0 meters to 3000 meters.

In particular, the injection of the coolant can cool the air upstream of the compression stage, thus increasing its density, and thus increasing the oxygen mass flow rate in the combustion chamber of the turbine. Furthermore, the vaporization of the cooling fluid in the combustion chamber can very significantly increase the pressure and/or the bulk density downstream of the combustion chamber and, therefore, increase the mechanical work recovered in the turbomachine. The density and viscosity of the coolant are thus varied according to pressure and temperature, atmospheric pressure and ambient temperature being relevant parameters to consider for adjusting the flow rate.

For example, the control is applied using a map (or table) that takes as input atmospheric pressure and/or ambient temperature and as output the flow rate to be injected. According to another example, control may be applied using a mapping table that takes as input parameters from atmospheric pressure and ambient temperature and the flow rate to be injected as output, and then makes any corrections via another mapping table or analytical calculation (or analytical function) that takes as input another parameter from atmospheric pressure and ambient temperature and the correction (to increase or decrease) of the flow rate as output. According to yet another example, control may be applied using an analytical calculation of the type "flow rate to be injected as a function of atmospheric pressure and/or ambient temperature". According to another example, control may be applied using an analytical calculation of the type "flow rate to be injected according to one of the two parameters from atmospheric pressure and ambient temperature", followed, where applicable, by a correction according to the other parameter from atmospheric pressure and ambient temperature, using a mapping table or another analytical calculation having the other parameter as input and the correction of the flow rate (to be added or subtracted) as output. For example, the control is applied using a fixed correction coefficient of the type of flow rate ═ function (atmospheric pressure, ambient temperature), or flow rate ═ function (atmospheric pressure) × depending on ambient temperature, or flow rate ═ atmospheric pressure, ambient temperature.

In certain embodiments, the flow rate of the injected coolant is adjusted such that the coolant/air mass ratio is between 0.5% and 15%, for example between 1% and 12%. This enables the power requirements to be adapted according to the flight envelope (altitude, temperature) or pilot requirements.

This allows the requirements of the flow rate to be injected to be accurately taken into account regardless of the point of the height/temperature envelope. In contrast, in the prior art only one point of the flow rate to be injected is considered, the size at one point of the height/temperature envelope is determined, and the flow rate to be injected is not recalibrated, and is therefore oversized in the rest of the envelope.

In certain embodiments, the flow rate of the injected coolant is adjusted as a function of at least one of a temperature of the coolant from inside the reservoir and a pressure of the coolant at a level of the injection manifold.

The characteristics of the coolant, such as its temperature and pressure, are parameters representative of its viscosity and density, and therefore advantageous parameters for regulating the flow rate. In other words, the physicochemical parameters of the fluid help to regulate the rated power (rating) of the electric pump, such as to ensure a proper flow rate.

In certain embodiments, the temporary power augmentation means is activated if a momentary power loss of the turbine is detected and/or if the turbine is detected to enter a predetermined rated power and/or if an additional power demand and/or user demand is detected.

This makes it possible to limit the consumption of coolant to the strictly necessary range by activating the temporary power increasing means only in the strictly necessary situation. For example, the activation of the temporary power increasing means may be automatic or manual. For example, by monitoring certain parameters, such as instantaneous power, rated power or power requirements, the temporary power increasing means may be automatically activated if a threshold is exceeded. The user may also determine that there is a demand for a temporary power increase and manually operate the temporary power increasing means.

In some embodiments, the temporary power increase means is activated according to: at least one parameter of the turbomachine, such as the rotational speed of the gas generator, the rotational speed of the low-pressure turbine or of the power turbine, the gas pressure at the outlet of the compressor stage, the temperature at the inlet of the low-pressure turbine or of the power turbine, the engine torque, and/or at least one parameter of the aircraft, wherein the turbomachine is configured such as the collective pitch of the helicopter rotors or the pitch of one or more turboprop engines to be assembled.

These parameters, considered individually or in combination, may represent a momentary power loss to the turbine, represent a predetermined rated power into the turbine and/or represent an additional power demand. Further, depending on the circumstances, the pilot may or may not authorize the temporary power augmentation device to automatically trigger the injection of fluid when necessary, or to maintain sole authority to determine activation of the injection of fluid.

In some embodiments, it is determined whether the temporary power increase means is activatable before activating the temporary power increase means.

This enables checking whether the temporary power adding means is available before attempting to use it, which enables saving coolant in the event that the temporary power adding means is not available in an attempt to use it. This also enables it to guarantee the effectiveness of the injection (sufficient fluid) and to inform the pilot when there is not sufficient fluid. In other words, this enables to guarantee the effectiveness of the injection and to inform the pilot of the availability of the functions.

In certain embodiments, it is determined whether the temporary power augmentation device is activatable according to at least one parameter from among a level of coolant inside the reservoir, a temperature of the coolant inside the reservoir, a pressure of the coolant at a level of the injection manifold, and a rotational speed of an electric pump of an injection circuit of the temporary power augmentation device.

These parameters, considered individually or in combination, may represent the availability of temporary power augmentation devices.

In certain embodiments, the activation of the temporary power augmentation device is stopped based on at least one parameter from among a level of coolant inside the reservoir, a temperature of the coolant inside the reservoir, an activation time of the temporary power augmentation device, an instantaneous power of the turbine, or a user request.

This makes it possible to limit the consumption of coolant to the strictly necessary extent. For example, the stopping of the power increasing means may be automatic or manual. For example, by monitoring certain parameters, such as the level of coolant inside the reservoir, the temperature of the coolant inside the reservoir, the activation time of the temporary power increasing means and/or the instantaneous power of the turbine, the temporary power increasing means may be automatically stopped if a threshold value is exceeded. The user may also decide that the temporary power increase is no longer needed and manually stop the temporary power increasing means.

One embodiment relates to a computer program comprising instructions for performing a method as claimed in any of the embodiments described herein.

The program may use any programming language and be in the form of source code, object code, or an intermediate code between source and object code, such as in partially compiled form, or in any other desired form.

One embodiment relates to a computer-readable recording medium having recorded thereon a computer program according to the present document.

The recording medium may be any entity or device capable of storing the program. For example, the medium may include a storage device such as a ROM, e.g., a CD-ROM or a microelectronic circuit ROM, or a magnetic recording device, e.g., a magnetic disk (floppy disk) or hard disk.

Alternatively, the recording medium may be an integrated circuit or a dedicated electronic card, into which the program is incorporated, the circuit or card being adapted to perform, or to be used for performing, the relevant method.

One embodiment relates to an integrated circuit or electronic card configured to perform a method according to the present disclosure.

Drawings

The subject matter herein and its advantages will be better understood after reading the detailed description of the different embodiments given below by way of non-limiting example. The present description relates to the pages of the drawings, in which:

figure 1 shows an aircraft equipped with twin turbines,

FIG. 2 shows the turbine of FIG. 1 in detail, an

FIG. 3 illustrates a method for controlling the turbine of FIG. 2.

Detailed Description

Fig. 1 shows a rotary wing aircraft 100, in this example a helicopter, having a main rotor 102 and a torque-resistant tail rotor 104 coupled to a propulsion assembly 50 for actuation thereof. The illustrated propulsion assembly 50 comprises two turbines 10, i.e. in this example two turbine shafts, the output shafts 12 of which are both connected to a main gearbox 106 for actuating a main rotor 102 and a tail rotor 104.

The turbine 10 is described in more detail with reference to fig. 2, and the present description applies to both turbines 10. The turbine 10 includes, from upstream to downstream, an intake housing 11, a high pressure compressor 12, a low pressure compressor 14, a combustor 16, a high pressure turbine 18, and a power turbine 20. High pressure compressor 12, low pressure compressor 14, combustor 16, and high pressure turbine 18 form a gas generator 15 configured to generate the gases required to drive a power turbine 20. The power turbine 20 drives rotation of an engine shaft 22 connected to a gearbox 24, which drives rotation of the shaft 12.

The turbine 10 has a temporary power augmentation device 26, including a coolant reservoir 26A and an injection circuit 26B. In this example, circuit 26B may have a pump 26B1 with a variable flow rate, a valve 26B2 with a fixed opening (on/off opening), and an injection manifold 26B 3. In this example, the pump 26B1 may be an electric pump and the valve 26B2 may be an electric valve. Thus, coolant flows from reservoir 26A to pump 26B1, then from pump 26B1 to valve 26B2, and then from valve 26B2 to injection section 26B 3. In this example, the injection portion 26B3 injects coolant upstream of the high pressure compressor 12 within the plenum of the intake housing 11. For example, the injection part 26B3 may be formed by a flushing hole of the housing 11. According to a variant, the injection portion can be opened further downstream, in a phase of vanes for guiding the intake air 13, also called inlet vanes (IGV).

In this example, the temporary power increase 26 is controlled by the control unit 30, which directly controls the pump 26B1 and the valve 26B 2. In this example, the control unit 30 may be a full authority digital electronic control (or FADEC) system of the turbine 10. The control unit 30 receives information from various sensors 32, the number and nature of which are not limited. The control unit 30 includes a ROM 30A forming a recording medium storing a computer program including instructions for executing a control method described below. In other words, when the computer program is executed by a computer, the control unit 30 forms one example of a computer, and the ROM 30A forms one example of a recording medium on which a computer program including instructions for executing a control method described below is recorded.

A method of controlling the turbine 10, or in other words, the temporary power increasing means 26 (hereinafter referred to simply as means), is described with reference to fig. 3. The method is performed by the control unit 30.

During a first step E1, it is determined whether the device 26 is activatable. In this example, it can be determined whether the device 26 is activatable according to a parameter set L1, the parameter set L1 parameters comprising the level Nf of the coolant inside the reservoir 26A, the temperature Tf of the coolant inside the reservoir 26A, the pressure Pf of the coolant at the level of the injection manifold 26B3, and the rotor speed Nep of the pump 26B1 of the injection circuit 26B of the temporary power increasing device 26. For example, the values of these different parameters may be measured in real time via the sensor 32.

If it is determined that the device 26 is no longer activatable ("NO" at step E1), for example because the level of coolant is too low, or because the pump 26B1 is not operating properly, the method terminates. In this example, when the method terminates, it will return to the beginning of step E1. For example, there may be a delay before beginning step E1 again. If it is determined that the device 26 is activatable ("yes" at step E1), the method proceeds to step E2.

During step E2, it is determined whether activation of device 26 is necessary. In this example, it can be determined whether the device 26 has to be activated or not, from a parameter set L2, which parameter set L2 comprises the rotation speed N1 of the gas generator 15, the rotation speed N2 of the power turbine 20, the gas pressure P3 at the outlet of the compressor 14 (i.e. at all stages of the compressor), the temperature T45 at the inlet of the power turbine 20, the engine torque TQ of the shaft 22, the total pitch XPC of the rotor 102, and any user request. For example, the values of these different parameters may be measured in real time via the sensor 32.

If it is determined that the device 26 does not need to be activated ("no" at step E2), the method terminates. In this example, when the method terminates, it will return to the beginning of step E1. For example, there may be a delay before beginning step E1 again. If it is determined that the device 26 must be activated (yes at E2), for example because one detects, based on the above parameters, that the turbine 10 is momentarily out of power or enters a predetermined rated power (rating) of the turbine 10 or a need for additional power, or a user request, then the device 26 is activated. To do so, the control unit may activate the pump 26B1 and open the valve 26B 2. The method then proceeds to step E3.

During step E3, the flow rate of coolant injected via manifold 26B3 is controlled. In this example, the flow rate can be controlled according to a parameter set L3, the parameter set L3 comprising the atmospheric pressure P0, the ambient temperature T0, the temperature Tf of the coolant inside the reservoir 26A, the coolant pressure Pf at the level of the injection manifold 26B3, the rotation speed N1 of the gas generator 15, the rotation speed N2 of the power turbine 20, the gas pressure P3 at the outlet of the compressor 14 (i.e. of all stages of the compressor), the temperature T45 at the inlet of the power turbine 20, the engine torque TQ of the shaft 22 and the overall pitch XPC of the rotor 102. For example, the values of these different parameters may be measured in real time via the sensor 32. To adjust the flow rate, the control unit 30 directly drives the flow rate delivered by the pump 26B 1. For example, the flow rate may be adjusted such that the coolant/air mass ratio is between 1% and 12%.

While adjusting the flow rate, the method proceeds to step E4, during which it is determined whether the device 26 may be stopped. For example, there is a delay between step E3 and step E4, but this is not required.

During step E4, it is determined whether the device 26 can be stopped. For example, it may be determined that the device 26 may be stopped according to a parameter set L4, the parameter set L4 comprising the level Nf of the coolant inside the reservoir 26A, the temperature Tf of the coolant inside the reservoir 26A, the activation time of the temporary power increasing device 26 (i.e. the time elapsed between the activation in step E2 and step E4), the instantaneous power of the turbine 10, or a user request. For example, the values of these different parameters may be measured in real time via the sensor 32.

If it is determined that it is not necessary to stop the device 26 ("NO" of step E4), the device 26 remains activated and the method returns to control step E3. For example, there may be a delay before beginning step E3 again. If it is determined that it is necessary to stop the device 26 ("yes" at step E4), for example, because there is no longer sufficient coolant in the reservoir 26A, because the device 26 has been active for a predetermined length of time, because the instantaneous power of the turbine is at an unacceptable threshold, or upon request by the user, the device 26 is stopped. For example, to stop the device 26, the control unit 30 stops the pump 26B1 and closes the valve 26B 2. The method is thus terminated and returns to the beginning of step E1. For example, there may be a delay before beginning step E1 again.

Although the present invention has been described with reference to specific embodiments, it will be apparent that modifications and variations can be made to these examples without departing from the general scope of the invention as defined in the claims. In particular, various features of the different embodiments illustrated/referred to may be combined in further embodiments. The specification and drawings are, accordingly, to be regarded in an illustrative rather than a restrictive sense.

It is also obvious that all features described with reference to the method can be converted into a device alone or in combination, and conversely all features described with reference to the device can be converted into a method alone or in combination.