• 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:

    公开号:FR3017601A1
    申请号:FR1551139
    申请日:2015-02-12
    公开日:2015-08-21
    发明作者:David G Bannon；William E Seidel
    申请人:Hamilton Sundstrand Corp；
    IPC主号:
    专利说明:

    [0001] AFTER-STOP RETRIEVAL SYSTEM FOR A HISTORIC DYNAMIC AIR TURBINE 100011 This disclosure relates to emergency booster power supplies for aeronautical applications, and more particularly to a dynamic air turbine for the generation of emergency booster power for an aircraft. airplane in flight. [0002] A dynamic air turbine (RAT) is a device for generating emergency backup power in a wide variety of aircraft. A RAT can produce a hydraulic current, an electric current, or both. A RAT includes a turbine that draws current from an airflow near the aircraft in flight. The turbine is coupled to appropriate power generation equipment, such as a hydraulic pump for the hydraulic power and an electric generator for the electric power. 100031 The location of the ATR in some aircraft is such that the deployment of the landing gear causes it to pass in front of the ATR, thereby blocking the flow of incoming air to the ATR. For RATs that power a hydraulic pump, reducing airflow can cause the RAT to stop. When the RAT stops, it can continue to run at low speed, typically at around 800 rpm, so that there is a balance between turbine torque and load torque. Once it is stopped, the RAT may not restart, even when the landing gear finishes its deployment and it no longer blocks the airflow to the RAT. SUMMARY 100051 In one aspect, a recovery system after stopping a dynamic air turbine comprises a dynamic air turbine, a hydraulic pump powered by the dynamic air turbine, the hydraulic pump having a pump inlet and a fuel outlet. pump, an electric generator powered by the dynamic air turbine, a bypass line that connects the pump inlet to the pump outlet, a bypass valve on the bypass line between the pump outlet and the pump outlet. pump inlet; and a control responsive to an input signal indicative of a potential shutdown state of the dynamic air turbine. The control causes the bypass valve to open to allow hydraulic fluid to flow through the bypass line to reduce pressure within the hydraulic pump. BRIEF DESCRIPTION OF THE FIGURES [0006] FIG. 1 is a diagram illustrating a recovery system after stopping a RAT system on an aircraft. DETAILED DESCRIPTION [0007] The system of recovery after stopping this disclosure solves the problem of failure to resume normal operation of the RAT system after a stop caused by a resistance (pump load torque) caused by a connected hydraulic pump. RAT system to provide hydraulic power. The after-recovery system allows the RAT to restart by creating a short circuit with the hydraulic fluid that reduces the resistance / pressure inside the hydraulic pump. Reducing the resistance / pressure inside the hydraulic pump reduces the pump load torque that the RAT system must overcome in order to return to normal operation and allow the RAT turbine system to turn more easily. Upon resuming normal operation, the short circuit is closed and the resistance / pressure is introduced into the hydraulic pump to provide hydraulic power to meet the hydraulic load demands of the aircraft system. [0008] FIG. 1 is a diagram illustrating the RAT 12 off-system. The RAT system 12 comprises a turbine 14, a gearbox 16, a generator 18, a hydraulic pump 20 (which includes a pump inlet 22 and a pump outlet 24), and a starting fuse 26. The turbine 14, the gearbox 16, the generator 18, and the hydraulic pump 20 can be connected to each other by a shaft 21. The RAT system 12 can be located on an aircraft that includes an aircraft system 28. An aircraft system 28 includes a hydraulic reservoir 30, a hydraulic load request 32, and a return 34. The hydraulic reservoir 30 is fluidly connected to the inlet of the pump 22 by a pump inlet line 31, while the load request 32 is fluidly connected to the outlet of the pump 24 via a pump outlet line 33. Even if it is not illustrated in FIG. FIG. 1, the return 34 may be fluidly connected to the hydraulic pump 20 and / or the hydraulic reservoir 30. In addition, the after-recovery system 10 may be located on an aircraft system 28 or a RAT system 12. In FIG. 1, the after-recovery system 10 is located on the aircraft system 28 and includes a control 36, a bypass circuit 38, which includes a bypass valve 40 and a bypass line 42. [0009] The control 36 receives input signals from the electric frequency sensor 44, the rotational speed sensor of the turbine 46 and / or the deployment sensor of the landing gear 48 and causes the opening or closing of the bypass 40 in response to a command 52 based on the received input signals. The RAT system 12 is deployed in emergency situations to provide electrical or hydraulic power to the components close to the RAT system 12, such as the components of the aircraft. When deployed, a high velocity fluid, such as air, causes the turbine 14 to rotate. The rotation of the turbine 14 drives the rotational energy transfer (RAT load torque) to the turbine. shaft 21 along which the gearbox 16, the generator 18 and the hydraulic pump 20 are located. The gearbox 16 rotates the shaft 21 to ensure that the rotational speed is within certain limits. The generator 18 transforms the rotational energy (RAT load torque) into a power supply that is transferred to various components. The hydraulic pump 20 converts the rotational energy (RAT load torque) into a hydraulic supply by pressurizing the hydraulic fluid that is transferred to the load demand 32 through the output line of the pump 33. [0011] in normal operating states of the RAT system 12, the hydraulic fluid is introduced into the hydraulic pump 20 through the hydraulic reservoir 30 through the inlet line of the pump 31. The hydraulic reservoir 30 can be fluidly connected to the load demand 32 by the return 34. After depletion of the hydraulic current by the load demand 32 provided by the load request 32, the return 34 completes the cycle of the hydraulic fluid by returning it to either the hydraulic pump 20 or to the hydraulic reservoir 30. [0012] During the initial deployment of the RAT system 12, the high velocity air acting on the turbine 14 may not produce sufficient load torque of the RAT. to overcome the resistance (load torque of the pump) on the shaft caused by the hydraulic fluid pressurized inside the hydraulic pump 20. Thus, the starting fuse 26 reduces the pressure inside the hydraulic pump 20 and allows the turbine 14 to turn more easily. Once the turbine 14 is in normal operating states, the starting fuse 26 is deactivated and the hydraulic pump 20 introduces a load torque of the pump on the shaft 21. During operation of the RAT system 12, several circumstances may cause the turbine 14 to slow down or stop, so that the load torque of the RAT produced by the turbine 14 is not sufficient to overcome the resistance on the shaft 21 by the hydraulic pump 20. shutdown prevents the generation of maximum electrical and hydraulic current and can lead to hazardous conditions in the aircraft due to the lack of power in important systems, such as guidance and control systems. Thus, it is important that the RAT system 12 includes a system that reduces the resistance on the shaft 21 and allows the turbine 14 to find operating states that produce a sufficient RAT load torque. This is achieved by the failover system 10, wherein the control 36 controls the bypass circuit 38 (through the control 52) to reduce the load torque of the pump as a function of the input signals from various inputs. components. The control 36 uses input signals to determine if the RAT system 10 is in a potential off state, or if it enters a potential off state, and takes appropriate steps to avoid stopping. When the control 36 determines that a stopping condition is occurring or can occur, it causes the bypass valve 40, which is on the bypass line 42, to open. The bypass 40 allows the hydraulic fluid inside the pump outlet line 33 to flow easily to the inlet line of the pump 31 because the bypass line 42 fluidly connects the outlet pump line 33 to the pump line 31. the inlet pump line 31. The bypass circuit (open bypass valve 40 and the bypass line 42) is configured to allow the load demand hydraulic fluid 32, the return 34, and the hydraulic reservoir 30 and flow easily from the outlet of the pump 24 to the inlet of the pump 22. The opening of the bypass valve 40 causes a rapid and significant decrease in pressure (and therefore the load torque) of the pump) to the inside The bypass valve 40 and the bypass line 42 must be sufficiently large to provide little resistance to the flow of hydraulic fluid through the circuit of the hydraulic pump 20 when the bypass valve 40 is opened. In another embodiment, the bypass line 42 may be configured to directly connect the inlet of the pump 22 and the outlet of the pump 24. The bypass valve 40 may be any combination which, when it is controlled , allows the flow of liquid through a line and, upon receipt of another command, to prevent a liquid from flowing through a line. When receiving an input signal that indicates that the stop state is complete or has not occurred, the control 36 causes the closing of the bypass valve 40. The closure of the Bypass valve 40 prevents hydraulic fluid from flowing through bypass circuit 38 and returns hydraulic pump 20 to normal operating states (pressure and pump load torque within the hydraulic pump 20 increase due to load demand 32, return 34, and hydraulic reservoir 30). The input signals from the control 36 may come from a number of components, including input signals not specifically mentioned in this disclosure. This disclosure describes some continuous input signals and some intermittent input signals. A continuous input signal is produced by the electric frequency sensor 44, which provides an input signal to the control 36 representing the electrical frequency of the power supply output of the generator 18. In a shutdown state the turbine 14 rotates at a slower speed than its rotational speed in normal operating states. This reduction in rotation speed produces less electric current than in normal operating states. The electric frequency sensor 44 provides information to the controller 36 so that the control 36 will determine if the RAT system 12 has entered a shutdown state when the power supply emitted by the generator 18 is reduced. When the input signal from the electric frequency sensor 44 indicates that the electric frequency produced by the generator 18 has decreased, the control 36 causes the bypass valve 40 to open (through the control 52). When the electrical frequency sensor 44 indicates that the electrical frequency has returned to normal, the control 36 may cause the bypass valve 40 to close. This is a continuous input signal because the electrical frequency sensor 44 continuously informs the control 36 of the electrical frequency / the output of the power supply. Another continuous input signal is the sensor of the rotational speed of the turbine 46. Instead of measuring the output of the power supply as the electrical frequency sensor 44, the sensor of the rotation speed of the turbine 46 senses the speed of rotation of the turbine 14 and informs the control 36. When the rotational speed falls below a specific level, the control 36 will determine whether or not the RAT system 12 has entered a state of rotation. stopping and may cause the bypass valve 40 to open (through control 52). When the rotational speed sensor of the turbine 46 indicates that the rotational speed of the turbine 14 has returned to normal, the control 36 may cause the closing of the bypass valve 40. As with the electric frequency sensor 44 the rotational speed sensor of the turbine 46 is a continuous input signal because it continuously informs the control 36 of the rotational speed of the turbine 14. 100191 An intermittent input signal is provided by the sensor deployment of the landing gear 48, which provides an input signal to the control 36 such that the aircraft is about to deploy the landing gear or is deploying the landing gear . The landing gear deployment sensor 48 may be useful on an aircraft that is configured so that the landing gear passes in front of the RAT system 12 during deployment.
    [0002] When this occurs, the landing gear can block the flow of high velocity fluid in the turbine 14 and reduce the rotational speed of the turbine 14 so that the RAT load torque is not sufficient to overcome the torque. charging the pump, resulting in a shutdown state. The landing gear deployment sensor 48 may be connected to the aircraft systems deploying the landing gear. When informed of the deployment of the landing gear, the landing gear deployment sensor 48 informs the control 36 of the potential stopping state and the control 36 may cause the bypass valve 40 to open. (through command 52). When the landing gear has completed its deployment, the control 36 closes the bypass valve 40. The control 36 may be aware that the landing gear has completed its deployment from an input signal from the landing gear. landing gear deployment sensor 48 or from a clocked signal in the control 36 which opens the bypass valve 40 for a predetermined period of time as a function of the known time that the landing gear deploys. The landing gear deployment sensor 48 is an intermittent input signal because it does not continuously inform the landing gear state control 36. 10020] The failover system 10 and the RAT system 12 may not include, include, or include all of the input signals and / or sensors described in this disclosure, based on redundancies, control systems, and control systems. other factors necessary for the aircraft. Discussion of Possible Embodiments [0022] The following are non-exclusive descriptions of possible embodiments of the present invention. A recovery system after a stop may comprise a dynamic air turbine, a hydraulic pump powered by the dynamic air turbine, the hydraulic pump having a pump inlet and a pump outlet, an electric generator powered by the turbine dynamic air flow, a bypass line that connects the pump inlet to the pump outlet, a bypass valve on the bypass line between the pump outlet and the pump inlet, and a control that responds to an input signal indicative of a potential shutdown state of the dynamic air turbine, the control being arranged to cause the bypass valve to open to allow hydraulic fluid to flow through the air line. bypass to reduce the pressure inside the hydraulic pump. The system of the preceding paragraph may optionally include, additionally and / or optionally, any of the following characteristics, configurations and / or components: [0025] The control is arranged to cause the opening of the bypass valve when the input signal indicates that the dynamic air turbine has entered a shutdown state. The control is arranged to control the bypass valve according to a frequency of the power supply generated by the electric generator. [0027] The control is arranged to cause the bypass valve to open when the input signal indicates that the electrical frequency is below a normal operating state and that the dynamic air turbine is in a state. stop. The control is arranged to cause the closing of the bypass valve when the input signal indicates that the electrical frequency is above a normal operating state and that the dynamic air turbine is not in a shutdown state. The control is arranged to cause the opening or closing of the bypass valve as a function of a measured rotational speed of the dynamic air turbine. The control is arranged to cause the opening of the bypass valve when the input signal indicates that the rotational speed of the dynamic air turbine is below a normal operating state and that the turbine to Dynamic air is in a shutdown state. The control is arranged to cause the closure of the bypass valve when the input signal indicates that the speed of rotation of the dynamic air turbine is at the same level or above a normal operating state and that the dynamic air turbine is not in a shutdown state. The dynamic air turbine is in an aircraft that comprises a landing gear, and the control is arranged to cause the opening of the bypass valve when the input signal, for example a signal from a landing gear deployment sensor indicates that the landing gear is being deployed. The dynamic air turbine is in an airplane which comprises a landing gear, and the control is arranged to cause the opening of the bypass valve when the input signal for example a signal from a landing gear deployment sensor, indicates that the dynamic air turbine is in a shutdown state. In another embodiment, a recovery system after stopping a dynamic air turbine may comprise a dynamic air turbine, a hydraulic pump powered by the dynamic air turbine, a bypass circuit fluidically connected to a hydraulic pump and a control which is arranged to control the bypass circuit according to the operating state of the dynamic air turbine, the operating state being indicated by at least one input signal, the control is arranged to causing the bypass circuit to reduce a pressure within the hydraulic pump when at least one input signal indicates that the dynamic air turbine has entered a potential shutdown state. The system of the preceding paragraph may optionally include, additionally and / or optionally, any of the following characteristics, configurations and / or components: [0036] The branch circuit comprises a bypass line which connects a pump outlet at a pump inlet and a control-driven bypass valve and configured to open to allow hydraulic fluid to flow through the bypass line and to close to prevent hydraulic fluid from flowing to through the diversion line. The control is arranged to control the branch circuit according to an electric frequency produced by an electric generator powered by the dynamic air turbine. The control is arranged to control the branch circuit according to a rotational speed of the dynamic air turbine. [0039] The recovery system after stopping the dynamic air turbine is on an aircraft which comprises a landing gear and a control which is arranged to control a bypass circuit according to the state of deployment of the train. landing.
    权利要求:
    Claims (15)
    [0001]
    CLAIMS: 1. Recovery system after stopping a dynamic air turbine comprising: a dynamic air turbine (14); a hydraulic pump (20) powered by the dynamic air turbine, the hydraulic pump comprising a pump inlet (22) and a pump outlet (24); an electric generator (18) powered by the dynamic air turbine; a bypass line (42) connecting the pump output to the pump inlet; a bypass valve (40) located on the bypass line between the pump outlet and the pump inlet; and a control (36) responsive to an input signal indicative of a potential shutdown state of the dynamic air turbine, the control being arranged to cause the bypass valve to open to allow the hydraulic fluid to flow. flow through the bypass line to reduce pressure inside the hydraulic pump.
    [0002]
    The system of claim 1, wherein the control (36) is arranged to cause the bypass valve (40) to open when the input signal indicates that the dynamic air turbine (14) has entered a stopping state.
    [0003]
    The system of claim 1 or 2, wherein the control (36) is arranged to control the bypass valve (40) according to a frequency of the power supply generated by the electric generator (18).
    [0004]
    The system of claim 3, wherein the control (36) is arranged to cause the bypass valve (40) to open when the input signal indicates that the electrical frequency is below a normal state of operation and that the dynamic air turbine (14) is in a shutdown state.
    [0005]
    The system of claim 3 or 4, wherein the control (36) is arranged to cause the bypass valve (40) to close when the input signal indicates that the electrical frequency is at or above the same level. a normal operating state and that the dynamic air turbine (14) is not in a shutdown state.
    [0006]
    6. System according to any one of claims 1 to 5, wherein the control (36) is arranged to cause the opening or closing of the bypass valve (40) according to a rotation speed of the dynamic air turbine measured.
    [0007]
    The system of claim 6, wherein the control (36) is arranged to cause the bypass valve (40) to open when the input signal indicates that the rotational speed of the dynamic air turbine is below a normal operating state and the dynamic air turbine is in a shutdown state.
    [0008]
    The system of claim 6 or 7, wherein the control (36) is arranged to cause the bypass valve (40) to close when the input signal indicates that the rotational speed of the dynamic air turbine (14) is at or above a normal operating state and the dynamic air turbine is not in a shutdown state.
    [0009]
    9. System according to any one of claims 1 to 8, wherein the dynamic air turbine (14) is in an airplane which comprises a landing gear, and the control (36) is arranged to drive the opening the bypass valve (40) when the input signal indicates that the landing gear is being deployed.
    [0010]
    The system of any one of claims 1 to 9, wherein the dynamic air turbine (14) is located in an airplane that comprises a landing gear, and the control (36) is arranged to drive the aircraft. opening the bypass valve (40) when the input signal indicates that the dynamic air turbine is in a shutdown state.
    [0011]
    A system for recovery after stopping a dynamic air turbine comprising: a dynamic air turbine (14); A hydraulic pump (20) powered by the dynamic air turbine; a bypass circuit (38) fluidly connected to a hydraulic pump; anda control (36) which is arranged to control the branch circuit according to an operating state of the dynamic air turbine, the operating state being indicated by at least one input signal, wherein the control is arranged to cause the bypass circuit to reduce a pressure within a hydraulic pump when at least one input signal indicates that the dynamic air turbine has entered a potential shutdown state.
    [0012]
    The system of claim 11, wherein the branch circuit (38) comprises a branch line (42) which connects a pump outlet (24) to a pump inlet (22) and a bypass valve (40). controlled by a control and configured to open to allow hydraulic fluid to flow through the bypass line and to close to prevent hydraulic fluid from flowing through the bypass line.
    [0013]
    The system of claim 11 or 12, wherein the control (36) is arranged to control the bypass circuit (38) based on an electrical frequency produced by an electric generator (18) powered by the dynamic air turbine. (14).
    [0014]
    The system of claim 11, 12 or 13, wherein the control (36) is arranged to control the bypass circuit (38) in accordance with a rotational speed of the dynamic air turbine (14).
    [0015]
    15. A system according to any of claims 10 to 14, wherein the dynamic air turbine stopping recovery system is on an aircraft which comprises a landing gear and a control (36) which is arranged for controlling the bypass circuit (38) according to the state of deployment of the landing gear.
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    同族专利:
    公开号 | 公开日
    US20150232194A1|2015-08-20|
    FR3017601B1|2019-04-19|
    US9561862B2|2017-02-07|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
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    US4722180A|1986-11-20|1988-02-02|United Technologies Corporation|Method and means for enhancing recovery of a surge condition in a gas turbine engine|
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    US7197870B2|2004-10-14|2007-04-03|Hamilton Sundstrand Corporation|Pressure/flow sensing stall recovery for a ram air turbine|CN107264812B|2016-04-08|2019-10-18|陕西飞机工业（集团）有限公司|A kind of aircraft emergency redundance power supply circuit|
    CN107128495A|2017-04-19|2017-09-05|中国航空工业集团公司金城南京机电液压工程研究中心|A kind of Ram Air Turbine Systems|
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    法律状态:
    2015-12-22| PLFP| Fee payment|Year of fee payment: 2 |
    2016-12-21| PLFP| Fee payment|Year of fee payment: 3 |
    2018-01-12| PLSC| Publication of the preliminary search report|Effective date: 20180112 |
    2018-01-23| PLFP| Fee payment|Year of fee payment: 4 |
    2020-01-22| PLFP| Fee payment|Year of fee payment: 6 |
    2021-01-20| PLFP| Fee payment|Year of fee payment: 7 |
    2022-01-19| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    US14185347|2014-02-20|
    US14/185,347|US9561862B2|2014-02-20|2014-02-20|Stall recovery system for a ram air turbine|
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