• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    turbomachinery and clearance control process on top of high pressure turbine blades in a turbomachinery. turbomachine comprising means for controlling the clearance between the tops of movable blades (16) of a high pressure turbine and an external housing (12) surrounding these blades (16), by cooling the external housing by air impact (48, 46) removed on a stage of the high pressure compressor of the turbomachine, and by electric heating (60) of the upper and lower parts of the external housing (12).
    公开号:BR112012005161B1
    申请号:R112012005161-0
    申请日:2010-09-07
    公开日:2020-09-01
    发明作者:Vincent Philippot
    申请人:Snecma；
    IPC主号:
    专利说明:

    [0001] The present invention relates to a turbomachinery, such as a turbo-reactor or an airplane turboprop, equipped with means for controlling the clearance at the top of blades as well as a process for controlling these clearances.
    [0002] In a classic way, the air passing through a turbomachine flows from upstream downstream through a low and high pressure compressor, then penetrates inside a combustion chamber whose outlet feeds a high pressure turbine whose rotor drives the high pressure compressor rotor then a low pressure turbine whose rotor drives the low pressure compressor rotor.
    [0003] The high pressure turbine generally comprises a wheel with movable paddles located between two rows of fixed paddles upstream and downstream carried by an external sump, a weak radial clearance being provided between the tops of the movable paddles and the outer sump . The movable wheel comprises a disc carrying the blades and connected to the high pressure turbine shaft.
    [0004] When operating the turbomachinery, it is important to minimize the radial clearance at the top of blades to prevent air leakage and ensure maximum turbomachinery performance.
    [0005] However, the adjustment of this radial clearance is delicate to carry out since the dimensional variations of the fixed parts in operation are different from the dimensional variations of the rotating parts. In effect, all parts are subjected to flue gas temperature variations that induce successive dilations and contractions depending on the engine regime, but the temperature variations and the corresponding dimensional variations of the rotating parts are slower than those of the fixed parts in ratio of thermal inertia and mass of the rotor disc of the high pressure turbine. On the other hand, it is also necessary to take into account the dimensional variations of the turbine blades due to the centrifugal forces in operation.
    [0006] Devices have been proposed for the control of clearances at the top of blades, which comprise means of removing air over an upstream part of the high pressure compressor, for example, over the fourth stage, and over a downstream part of this compressor. , for example, on the ninth stage. Each air removal circuit comprises a valve whose opening and closing of the valves is controlled by a regulation system. The air thus removed is conducted to the external sump to cool or heat it and thus regulate the clearances at the tops of the mobile blades of the high pressure turbine (see the applicant's document FR2828908-A1).
    [0007] The regulation system receives information related to the turbomachinery regime, the temperature of the external crankcase, the temperature at the outlet of the high pressure compressor, as well as information regarding the operation of the turbomachinery (idling on the ground, hot start or cold, temporary acceleration or deceleration, ...).
    [0008] This known device is complex since it requires the installation of valves and separate air removal circuits in parts upstream and downstream of the high pressure compressor. It is necessary to control the degree of opening of the valves to perfectly control the temperature of the air destined to impact the external crankcase, which proves to be equally complicated. In addition, this type of device proves to be particularly heavy and uncomfortable. Finally, the removal of air over the downstream part of the high pressure compressor is disadvantageous because it consumes air at very high pressure and impairs the performance of the turbomachinery.
    [0009] Another problem arises in the case of a hot restart of the turbomachine, that is, when the turbomachine is started after an insufficient stopping time so that the temperature of the turbomachinery and in particular that of the rotor disc of the turbocharger. high pressure turbine are resumed at room temperature. After stopping the turbomachinery, it is observed that it cools down more quickly (in six hours in relation to the quadrant of a clock) than in the upper part (in twelve hours in relation to the quadrant of a clock), which leads to an eccentricity of the high pressure turbine rotor in the outer crankcase. As a result, the clearance in the tops of the lower blades is reduced and the centrifugation of the rotor blades of the high pressure turbine can lead to friction on the outer crankcase in a lower position.
    [0010] It has also been proposed a device for controlling the clearances by electrically heating the external crankcase, which allows absorbing accelerations and avoiding the harmful effects of hot start-ups, but does not allow the crankcase to be cooled to reduce clearances in cruise flight .
    [0011] The invention is notably intended to provide a simple, effective and economical solution to these problems of the prior art.
    [0012] For this purpose, it proposes a turbomachine comprising means for controlling the play between the tops of the movable blades of a high pressure turbine and an external crankcase surrounding these blades, comprising means of cooling the external crankcase by the impact of air removed in a stage of the high-pressure compressor of the turbomachine, characterized by the fact that it comprises first means of electric heating of the upper part of the external housing and second means of electric heating of the lower part of the external housing, as well as means of all-or-nothing control air-cooling means and independent means of controlling the first means and the second means of electric heating.
    [0013] The invention, combining means of cooling the crankcase by air impact and means of electric heating of the crankcase, allows to benefit from the advantages of these two systems, while avoiding their respective drawbacks.
    [0014] The integration of the electric heating means of the external crankcase makes it possible to suppress the hot air removal circuit in the downstream part of the high pressure compressor and therefore improves the performance of the turbomachinery.
    [0015] The operation of all-or-nothing air impact cooling means allows simplifying the design of the clearance control means because it is no longer necessary to control the degree of opening of a valve as in the prior art.
    [0016] On the other hand, the independent operation of the electric heating means of the upper part and the lower part of the crankcase makes it possible to bring a solution to the problem of the hot restart of the turbomachine only by specifically commanding the heating of the lower part of the external crankcase to avoid contacts with the tops of the high pressure turbine rotor blades.
    [0017] According to another characteristic of the invention, the air impact cooling means comprise a ring carried by the external housing and comprising axially spaced protuberances between which multi-perforated ramps of removed air are installed over the high pressure compressor. pressure.
    [0018] The means of removing air over the high pressure compressor may comprise a means of opening and closing the arrival of air over the external housing.
    [0019] In a particular embodiment of the invention, the cooling air is removed from the fourth stage of the high pressure compressor and its flow rate is in the order of 0.7% of the total air flow rate in the compressor.
    [0020] In an embodiment of the invention, the electrical heating means comprise resistive circuits carried by the external housing on the upper and lower parts thereof.
    [0021] With advantage, the resistive circuits are mounted in the vicinity of the protuberances of the ring carried by the external housing.
    [0022] The invention also relates to a process of controlling the play in the top of high pressure turbine blades in a turbomachine as previously described, this process consisting, when a hot restart of the turbomachine, in activating the maximum power of the electric heating means of the lower part of the high pressure turbine housing and in disabling the heating means of the upper part of this housing.
    [0023] Thus, only the electric heating means of the lower part are activated in the case of hot restart, to avoid an increase in the clearances at the blade tops and a decrease in the turbine efficiency.
    [0024] This process also consists of a cold start of the turbomachine, activating the heating means of the lower part of the external crankcase to a power equal to 50% of its maximum electrical power.
    [0025] At the beginning of a phase of increasing the turbomachinery regime after a hot start, the power of the electric heating means of the lower part is temporarily decreased by about 50% of the maximum electric power mentioned above, the electric power increasing afterwards until it reaches about 75% of the maximum electrical power.
    [0026] Similarly, at the beginning of a phase of increasing the turbomachinery's regime after a cold start, the electric heating means of the lower part are temporarily deactivated and then reactivated to reach a power equal to 75% of its maximum electrical power. .
    [0027] This decrease in heating when starting hot or cold at the beginning of the increase in the system avoids a very rapid expansion of the external crankcase in relation to that of the high pressure turbine rotor and therefore prevents an increase in clearance in the start of the increase in the turbomachinery regime that would aggravate air leaks at the top of the blades.
    [0028] According to another characteristic of the process according to the invention, the electric heating means of the lower part of the external crankcase are activated at full power prior to a lowering of the turbomachinery regime in the cruising phase to avoid a very rapid contraction of the external sump due to the lowering of the temperature in the primary chain and thus preventing contacts on the tops of blades.
    [0029] Advantageously, during the cruise phase, all the electric heating means of the external crankcase are deactivated and the air impact cooling means are activated.
    [0030] The invention will be better understood and other details, advantages and characteristics of the invention will appear in the reading of the following description made, by way of non-limiting example, with reference to the attached drawings, in which: - figure 1 is a schematic view partial axial section of a high-pressure turbine and a clearance control device at the top of blades according to the prior art; figures 2A and 2B are schematic representations of the turbomachine when cold and hot restarting; figure 3 is a partial schematic view in axial section of a high pressure turbine and of a device for controlling the play at the top of blades according to the invention; figure 4 is a graphical representation representing the variations in the power of electric heating means of the lower part of the turbomachinery according to the invention.
    [0031] Reference is made first to Figure 1, which represents an upper part of a high-pressure turbine disposed out of a combustion chamber and upstream of a low-pressure turbine and comprising an external sump 12 and a wall 14 outwardly delimiting the flow of primary air flow in which a wheel with movable blades 16 rotates mounted between two rows of fixed blades upstream 18 and downstream 20. Wall 14 is formed by annular segments 22, 24 bearing the fixed blades 18, 20 and by annular segments 26 arranged between the annular segments 22, 24 and in front of the radially external ends of the movable blades 16 carried by a high pressure turbine rotor disc (not shown).
    [0032] A ring 28 is inserted between the outer housing 12 and the wall 14 and at its upstream end comprises a radial clamp 30 for fixing by pins on a protrusion 32 of the outer housing 12, the downstream end comprising a radial clamp 34 clamped between a radial clamp 36 of the downstream end of the outer crankcase 12 and a radial clamp 38 of the downstream end of a downstream turbine housing 40. This ring 28 supports by means of a clamp 42 the annular segments 26 surrounding the movable blades 16 and comprises a plurality of protuberances 44 axially spaced from each other and between which multi-perforated ramps 46 are installed.
    [0033] Clearance control means between the tops of the blades 16 and the annular segments 26 comprise a cold air removal circuit 48 over an upstream part of the compressor, for example, over the fourth compression stage and a removal circuit of hot air 50 over a part downstream of the compressor, for example, over the ninth compression stage. Each cold air 48 and hot air 50 removal circuit is connected at the outlet to a valve 52, 54 which controls the flow rate removed in cold air and hot air. A conduit 56 connected to the outlet of the valves allows to inject the air mixture removed in the high pressure compressor in the multi-perforated ramps 46 through which the air is ejected and impacts the ring 28 to cool or heat it.
    [0034] A third air removal circuit 57 over the fourth stage of the high pressure compressor is planned to cool the low pressure turbine. For this purpose, the cold air removed is injected directly into the flow stream of the primary air flow through the external housing 12 and passes through the holes 58 of the ring 28 that flow at the level of the fixed blade alignment 20. The flow rate of this cooling air is on the order of 2% of the total air flow rate of the high pressure compressor.
    [0035] In general, it is well understood that the cooling or heating of the ring by air impact removed in the high pressure compressor induces a cooling or heating, respectively, of the outer housing 12 and of the ring 28. This heating or cooling allows to control the radial position of the annular segments 26 in relation to the movable paddles 16 and, therefore, the clearances in the tops of the movable paddles 16.
    [0036] The control of the mixture of cold air and hot air impacting ring 28 is carried out by means of a digital regulation system with full authority (or FADEC in English) of the turbomachine that takes into account a plurality of information such as, for example, the operating mode of the turbomachine, the temperature of the external crankcase 12 and the time of stopping the turbomachine between two uses, to determine the proper opening of the valves 54, 52 and thus minimize the clearance at the top of the blades 16.
    [0037] For example, when the turbomachinery is cold starting and at slow speed on the ground, the outer crankcase 12 and the rotor disc of the high pressure turbine are in thermal equilibrium (figure 2A). The high pressure turbine rotor 59 is thus centered inside the outer crankcase 12. Due to the thermal inertia of the high pressure turbine rotor disk and the faster expansion of the outer crankcase 12, it is necessary in this configuration to cool the outer crankcase 12 to prevent an increase in clearance at the blade tops. Thus, the regulation system controls the opening of the cold air removal valve 52 over the fourth compression stage and commands the closing of the hot air removal valve 54 over the ninth compression stage. The removed air is then directed to the multi-perforated ramps 46 and leaves them to impact the protrusions 44 of the ring 28 and cool the ring 28 and the external sump.
    [0038] However, these means of cooling and heating by air impact on the outer casing 12 work uniformly over the entire circumference of the high pressure turbine, that is, that the entire circumference of the ring 28 is impacted by a single and same mixture of air from the high pressure compressor, which is not satisfactory in case of hot restart of the turbomachinery.
    [0039] In effect, the outer casing 12 cools more quickly than the rotor disc of the high pressure turbine (it takes about 5 hours for the disc to be cooled), and the turbomachine cooling is faster at the bottom that in the upper part, there is a decentralized configuration (“excentration”) of the high pressure turbine rotor 59 inside the external housing 12 (figure 2B). In the case of hot restart, the clearances at the top of the blades in the lower position are very low and the effect of the centrifugal force on the rotor of the high pressure turbine leads, by increasing the radial dimension of the mobile blades 16, to contacts in a lower position between the radially outer ends of the movable paddles 16 and the annular segments 26 located in front of them.
    [0040] The use of means of controlling air gap play as previously described would lead to a uniform expansion of the entire circumference of the external sump 12 and, therefore, to excessively increase the clearances at the top of blades in part top of the turbomachinery.
    [0041] The invention presents a solution to this problem as well as to those previously mentioned by removing the hot air removal means 50 over the high pressure compressor and replacing them with first electric heating means of the upper part of the external housing 12 independently controlled of seconds electric heating means of the lower part of the external housing 12. The electrical heating of the external housing 12 proves to be faster and, therefore, more reactive than the heating by impact of hot air and does not decrease the performances of the high pressure compressor of the turbomachinery.
    [0042] The first and second electric heating means 60 of the upper and lower part of the external housing 12 are mounted in the vicinity of the protrusions 44 of the ring 28 as shown in figure 3 and can be resistive type circuits.
    [0043] Control means independent of the first and second electric heating means 60 are provided and are connected to the regulation system in order to independently control the heating of the lower and upper parts of the external housing 12, which allows to answer the problem of restarting the turbomachinery as explained in more detail below.
    [0044] The cooling of the external housing 12 is carried out by means of cooling by air impact as previously described, that is, by means of an air removal circuit 48 over the fourth stage of the high pressure compressor, this air feeding the multi-perforated ramps 46 and being ejected towards the protrusions 44 of ring 28. Unlike the prior art, the cooling means may comprise an all-or-nothing control valve 61 by means of control means 63 connected to the control system regulation.
    [0045] Figure 4 is a graphical representation representing the variations of the power of the electric heating means of the lower part of the turbomachine when a cold restart in stippling and when a hot restart in full stroke.
    [0046] To avoid contacts on the blade tops at the bottom of the turbomachine when hot restarting, the electric heating means at the bottom of ring 28 are activated at full power at 62, which allows the ring to expand and so increase the clearances at the top of paddles in this part. At the same time, the electric heating means of the upper part of the ring 28 are deactivated since the clearances in the tops of blades 16 in this location are sufficient as previously explained, which prevents an increase in the clearances in the top of blades in the upper part that would degrade the performance of the turbomachinery.
    [0047] After a hot start and at the beginning of a phase of increasing the turbomachinery regime, the electric heating means of the lower part are temporarily fed to about 50% of its maximum power in 64, which prevents an increase in clearances due to a rapid expansion of the external sump 12 due to the combined effect of electric heating and the increase in the temperature of the gases in the primary current as a result of the increase in the regime.
    [0048] The electrical power is then progressively re-increased by 66 until it reaches about 75% of the maximum power 68 to readjust the clearances at the blade tops due to the progressive expansion of the high pressure turbine rotor disc.
    [0049] The invention is also usable when a cold start of the turbomachinery (figure 4). In this case, the electric heating means of the lower part are activated at full power for a short period 70 (typically 3 seconds) until the idling speed is established on the ground, after which its power is reduced by 72 to 50% of the maximum power. In fact, during the period of idling on the ground, it is not necessary to strongly expand the lower part of the external sump since the rotor of the high pressure turbine is not eccentric inside the external sump 12.
    [0050] At the beginning of the increase in the turbomachinery regime after a cold start, the electric heating means of the lower part are temporarily deactivated in 74 to avoid a rapid expansion of the external sump as explained above in reference to an increase in the regime after a hot restart.
    [0051] The electrical power is then gradually increased by 76 until it reaches about 75% of the maximum power in 68 to readjust the clearances at the top of blades due to the progressive expansion of the high pressure turbine rotor disc.
    [0052] The electrical heating means of the lower part of the external crankcase 12 are activated at full power at 78 prior to a low of the cruise phase regime whether the turbomachinery has been started cold or hot. This avoids a very rapid contraction of the external sump and allows it to be kept at a sufficient temperature for the time necessary to decrease the radial dimensions of the movable paddles due to the drop in temperature as a result of the regime drop.
    [0053] When cruising at 80, the electric heating means are deactivated and only the air impact cooling means are activated and the valve is placed in an open position.
    [0054] It is thus possible with the invention to have means of cooling by air impact that only work in the cruise phase and under an all-or-nothing control operating mode that is very simple to implement.
    权利要求:
    Claims (12)
    [0001]
    1. Turbomachine comprising means of controlling the play between the tops of the movable blades (16) of a high pressure turbine and an external housing (12) surrounding these blades (16), comprising means of cooling the external housing by air impact ( 48, 46) removed from a high-pressure compressor stage of the turbomachinery, characterized by the fact that it comprises first electric heating means (60) of the upper part of the external housing (12) and second electric heating means of the lower part of the housing external (12), as well as all-or-nothing control means (63) of the air impact cooling means (48, 61, 46) and independent control means of the first means and the second electric heating means (60 ).
    [0002]
    2. Turbomachinery, according to claim 1, characterized by the fact that the air impact cooling means (48, 46) comprise a ring (28) carried by the external housing (12) and comprising protrusions (44) axially spaced between which multi-perforated ramps (46) are installed for the air outlet removed from the high pressure compressor.
    [0003]
    3. Turbomachinery according to claim 1 or 2, characterized by the fact that the air removal means (48) on the high pressure compressor comprise a valve (61) for opening and closing the air inlet on the external sump (12).
    [0004]
    4. Turbomachinery according to any one of claims 1 to 3, characterized by the fact that the cooling air is removed over the fourth stage of the high pressure compressor and its flow rate is in the order of 0.7% of the total air flow rate in the compressor.
    [0005]
    Turbomachinery according to any one of claims 1 to 4, characterized by the fact that the electric heating means (60) comprise resistive circuits carried by the external housing (12) on the upper and lower parts thereof.
    [0006]
    6. Turbomachinery according to claims 2 and 5, characterized by the fact that the resistive circuits are mounted in the vicinity of the protrusions (44) of the ring (28) carried by the crankcase (12).
    [0007]
    7. Process for controlling clearances at the top of high-pressure turbine blades in a turbomachine as defined in any one of claims 1 to 6, characterized by the fact that it consists, when hot restarting the turbomachine, of activating at maximum power the electric heating means (60) of the lower part of the housing (12) of high pressure turbine and disable the heating means (60) of the upper part of this housing.
    [0008]
    8. Process, according to claim 7, characterized by the fact that, at the beginning of an increase phase of the turbomachinery regime after a hot start, the power of the electric heating means (60) of the lower part is temporarily decreased to about 50% of the maximum electrical power, the electrical power then increasing until it reaches about 75% of the maximum electrical power.
    [0009]
    9. Process according to claim 7 or 8, characterized by the fact that, when the turbomachine is cold started, it activates the electric heating means (60) of the lower part of the external housing (12) at a power equal to 50% of its maximum electrical power.
    [0010]
    10. Process according to claim 9, characterized by the fact that, at the beginning of an increase phase of the turbomachinery regime after a cold start, the electric heating means (60) at the bottom are temporarily deactivated then reactivated with a power equal to 75% of its maximum electrical power.
    [0011]
    11. Process according to any one of claims 7 to 10, characterized by the fact that the electric heating means (60) of the lower part of the external crankcase are activated at full power prior to a reduction of the turbomachinery regime in the cruise phase .
    [0012]
    12. Process according to any one of claims 7 to 11, characterized by the fact that it consists, during the cruising phase, of deactivating all the electrical heating means of the external crankcase and activating the cooling means by air impact
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    法律状态:
    2019-01-08| B06F| Objections, documents and/or translations needed after an examination request according art. 34 industrial property law|
    2019-10-08| B06U| Preliminary requirement: requests with searches performed by other patent offices: suspension of the patent application procedure|
    2020-06-30| B09A| Decision: intention to grant|
    2020-09-01| B16A| Patent or certificate of addition of invention granted|Free format text: PRAZO DE VALIDADE: 20 (VINTE) ANOS CONTADOS A PARTIR DE 07/09/2010, OBSERVADAS AS CONDICOES LEGAIS. |
    优先权:
    申请号 | 申请日 | 专利标题
    FR09/04275|2009-09-08|
    FR0904275A|FR2949808B1|2009-09-08|2009-09-08|PILOTAGE OF THE AUBES IN A TURBOMACHINE|
    PCT/FR2010/051855|WO2011030051A1|2009-09-08|2010-09-07|Clearance control at the blade tips of a turbomachine|
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