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CN-116438366-B - Device for controlling an air flow guiding system, in particular in an aircraft turbine engine

CN116438366BCN 116438366 BCN116438366 BCN 116438366BCN-116438366-B

Abstract

An apparatus (30) for controlling an air flow guiding system (20), the apparatus comprising at least one actuator (31) configured to translate a control lever (32) between a first end position and a second end position of a nominal operating range, wherein at least one blade (21 a) of the air flow guiding system (20) is movable between a first angle and a second angle, the control lever (32) being connected to the blade (21 a) by a control lever (33) comprising a first control link (36) and a second control link (37) hinged together. The actuator (31) is configured to bring the control lever (32) into a safety position outside the second end position of the nominal working range and to orient the blade (21 a) at a safety pitch angle between the first angle and the second angle.

Inventors

  • Frederick Anthony Alan Inburg
  • Pierre Shabana
  • Tibo Maxim Javoy

Assignees

  • 赛峰直升机发动机公司

Dates

Publication Date
20260512
Application Date
20211110
Priority Date
20201110

Claims (7)

  1. 1. A control device (30) for controlling an air flow guiding system (20) comprising at least one blade (21 a) movable around an axis of rotation between a first angle (alpha 1) and a second angle (alpha 2), the control device (30) comprising at least one actuator (31) configured to drive a control lever (32) in translation between a first end position (P1) and a second end position (P2) of a nominal working range, wherein the blade (21 a) is movable between the first angle (alpha 1) and the second angle (alpha 2), the control lever (32) being connected to the axis of the blade (21 a) by a control lever (33) hinged with respect to a free end of the control lever (32) opposite to the end connected to the actuator (31), The control lever (33) comprises a first control link (36) and a second control link (37), the first control link (36) comprising a first end (36 a) hinged with respect to a free end of the control lever (32) and a second end (36 b) hinged with respect to a first end (37 a) of the second control link (37), the second control link (37) further comprising a second end (37 b), the second end (37 b) of the second control link being opposite to the first end (37 a) of the second control link and being fixed for rotation with the blade (21 a), and the actuator (31) being configured to bring the control lever (32) into a safety Position (PS) outside a second end position (P2) of the nominal working range and to orient the blade (21 a) at a safety pitch angle (aS) between the first angle (a1) and the second angle (a2), Wherein the control lever (33) comprises only the first control link (36) and the second control link (37), and the first control link and the second control link are hinged together by a ball joint connection, Wherein the air flow guiding system (20) comprises a plurality of variable pitch stator blades (21), the plurality of variable pitch stator blades (21) comprising a main blade (21 a) and a plurality of auxiliary blades (21 b), the main blade being connected to the control lever (33), the movement of the plurality of auxiliary blades being synchronized with the movement of the main blade (21 a), the control device (30) further comprising a control ring (34) connected to the control lever (33) and to the auxiliary blade (21 b) by an auxiliary link (35), the rotational axes of the main blade (21 a) and the auxiliary blade (21 b) being perpendicular to the axis of the control ring (34), and Wherein the length of the second control link (37) is substantially equal to the length of the secondary link (35), the control ring (34) being hinged on the second control link (37) at a point coinciding with a ball joint connection between the first control link (36) and the second control link (37).
  2. 2. The control device (30) according to claim 1, wherein the actuator (31) is configured to transmit pure axial movement to the control rod (32) according to the movement axis (X-X') of the actuator (31).
  3. 3. The control device (30) according to claim 1 or 2, wherein the actuator (31) comprises an actuator rod connected to the control rod (32) by a rigid connection.
  4. 4. The control device (30) according to claim 1 or 2, wherein the actuator (31) is a cylinder comprising a body defining a cylindrical chamber in which a piston is translationally mounted, one end of the piston being connected to the control rod (32), the piston being configured to perform an overtravel when the control rod (32) is moved into the safety Position (PS).
  5. 5. A turbine engine (10) of an aircraft comprising, from upstream to downstream in the flow direction of an air flow, an inlet sleeve (11) receiving air, a centrifugal compressor (12), an annular combustion chamber (13) downstream of the compressor (12), a high-pressure power turbine (14) intended for driving the compressor (12) in rotation, an output turbine (16) intended for driving an output shaft (17) in rotation, an air flow guiding system (20) upstream of the compressor (12), and a control device (30) for controlling the air flow guiding system (20) according to any one of claims 1 to 4.
  6. 6. The turbine engine (10) of claim 5, wherein the rotational axis of the blades (21 a) of the airflow directing system (20) is perpendicular to the central axis (a) of the turbine engine (10).
  7. 7. Single-engine helicopter comprising a turbine engine (10) according to claim 5 or 6.

Description

Device for controlling an air flow guiding system, in particular in an aircraft turbine engine Technical Field The present invention relates to the field of aircraft, in particular aircraft turbine engines. More particularly, the present invention relates to control of airflow directing systems. Background Generally, turbine engines include a compressor, a combustor located at an outlet of the compressor, a high pressure turbine intended for driving the compressor in rotation, and a low pressure turbine intended for driving blades of an aircraft in rotation. The turbine engine also includes an air flow guiding system, so-called "inlet guide vanes (inlet guide vane)", abbreviated as "IGV", comprising a plurality of fins or variable-pitch inlet guide vanes, positioned upstream of the compressor and allowing to increase the efficiency of the compressor, thus increasing the thermodynamic cycle of the engine at cruising speed. Such a system helps to reduce fuel consumption of the aircraft. By "variable pitch" is understood that the angular position of all blades of the same stage is synchronized by means of a control ring or control crown fixed to all blades. Each blade is connected to a control ring via a control link. It is known to control the position of the vane by means of a cylinder system fastened to the housing and comprising a piston movable in a cylinder chamber between two end positions of the nominal operating range of the engine, which piston is connected to the control crown via a control rod. The vanes are continuously movable between a first angle and a second angle during movement of the piston between the first end position and the second end position. In general, the control of the piston movement is performed by means of a fluid distributor, for example by means of an oil separator in the case of hydraulic control. In case of failure of a component of the blade control kinematics, the position of the piston and thus the pitch angle (PITCH ANGLE) of the blade will no longer be known. It is necessary to know the position of the piston and thus the pitch angle of the blade at any time and to achieve this in a reliable manner. Disclosure of Invention The present invention therefore aims to overcome the drawbacks of the control devices of the above-mentioned air flow guiding systems. The object of the invention is to improve safety in the event of failure of a vane control kinematic element. The object of the present invention is therefore an apparatus for controlling an air flow guiding system comprising at least one blade, which is movable in rotation about an axis of rotation between a first angle and a second angle, the control apparatus comprising at least one actuator configured to drive a control rod in translation between a first end position and a second end position of a nominal operating range, wherein the blade is movable between the first angle and the second angle, the control rod being connected to the axis of the blade by a control lever, which control lever is hinged with respect to a free end of the control rod, which free end of the control rod is opposite to an end connected to the actuator. The control lever includes a first control link and a second control link. The first link includes a first end hinged relative to the free end of the control rod, and a second end hinged relative to the first end of the second link, the second link further including a second end opposite the first end of the second link, the second end of the second link being fixed for rotation with the blade. In case of a failure of the control device, the actuator is configured to bring the control lever into a safety position outside the second end position of the nominal working range and orient the blade at a safety pitch angle between the first angle and the second angle. The safety position and the safety pitch angle correspond to a so-called safety position, which enables the air flow to pass even in case of a malfunction of the control device. Thus, in case of a failure of the control device, the position of the piston and the pitch angle of the blade are known at any time and this is achieved in a reliable manner. Advantageously, the actuator is configured to transmit pure axial movement to the control rod according to the axis of movement of the actuator. According to one embodiment, the control lever comprises only a first control link and a second control link, and the first control link and the second control link are hinged together by a ball joint connection (ball joint connection). The air flow guiding system may be of the type having inlet guide vanes, or so-called "inlet guide vanes" with variable pitch, abbreviated to "IGVs", comprising a number of stator fins or stator vanes comprising a main vane connected to a control lever, and a number of secondary vanes, the movement of which is synchronized with the movement of the main vane, the control device further comprising a control ring