Gas turbine fan engine compressor guide vane actuator cylinder structure and method

Abstract

The invention discloses a gas turbine fan engine compressor guide vane actuator cylinder structure and method.The structure comprises a pipe connecting head A, a pipe connecting head B, a shell, a cavity, an end cover, a piston, an adjusting assembly, a driving assembly and a plurality of small fixing parts, and the shell is provided with a plurality of holes so that an actuator cylinder can be fixedly installed on an engine; and the pipe joint A and the pipe joint B are respectively connected with the shell and are arranged at two ends of the upstream and downstream flow paths. Compared with a traditional actuator cylinder structure, the actuator cylinder structure is higher in function error-tolerant rate, hydraulic driving force for pushing the guide vane of the gas compressor to act is effectively provided, displacement signals of the angle of the actuator cylinder are fed back to an engine electronic controller, and the controller can conduct closed-loop control over the angle of the guide vane of the gas compressor; the error between the indication position of the rocker arm pointer and the actual control precision can be corrected to be not more than + / -1% according to the adaptability of the adjusting screw, and the robustness between the RVDT feedback value of the guide vane actuator cylinder and the actual angle of the actuator cylinder is good.

Description

Technical Field

[0001] The invention belongs to the technical field of aviation engines, and in particular relates to a compressor guide vane actuator structure and method for a gas turbine fan engine. Background Art

[0002] In order to meet the requirements of safe operation of aircraft engines under high speed, high temperature, variable load and other conditions, the compressor inlet is usually designed with multi-stage continuously adjustable blades to achieve overall engine matching and high and low pressure flow stability, which puts higher requirements on the fault tolerance of hydraulic actuators. Existing compressor guide vane actuators are divided into electronically controlled and hydraulic types. Regardless of the type, due to structural defects, their mechanical limit capacity and adjustment control capabilities deviate from the design requirements. In engineering, the focus is generally on whether the consistency of engine thrust meets the aircraft power requirements, and few structural types have been used to overcome the problem of mechanical limit defects.

[0003] The patent document with publication number CN113700676A discloses a self-bleeding controlled gas turbine compressor adjustable guide vane adjustment drive mechanism, which mainly includes a main actuator, an auxiliary actuator and a connecting pipeline. The main actuator and the auxiliary actuator control the movement of the piston through a high-pressure air source drawn from the compressor casing. The higher the speed of the gas turbine, the greater the bleed air pressure of the adjustable guide vane adjustment drive mechanism, the greater the piston displacement of the actuator, and the greater the rotation angle of the adjustable guide vane.

[0004] The patent document with publication number CN114183252A discloses a main actuator of a gas turbine rotatable guide vane rotation mechanism, including a control actuator, a control piston, a control spring, a pipe joint for high-pressure air bleed, a power cylinder, a power piston, a pipe joint for low-pressure air bleed, a power spring, a pipe joint for bleed air to an auxiliary actuator, an inner cavity L of the control actuator, a power piston cavity M, a gap H, a power spring cavity P, a hole D and a flow limiting nozzle E. The control actuator is connected to the power cylinder through an adapter, and the adapter cooperates with a nut on the control actuator. The invention adopts high-pressure air inside the gas turbine compressor as the power source of the rotatable guide vane mechanism, reducing the redundancy of the external power source. When the surge margin of the gas turbine is low, the control actuator controls the power piston to move, pushes the rotatable guide vane actuator to realize the rotation of the rotatable guide vane, and realizes adaptive adjustment of the compressor working condition and the action of the rotatable guide vane.

[0005] The above patents are all controlled by air pressure, and the piston is connected to the spring to achieve the corresponding control effect, but the control type and structure are different from those of the present application. Summary of the invention

[0006] Based on the above background, a gas turbine fan engine compressor guide vane actuator structure and method are proposed, which can achieve high-performance position tracking control and active fault tolerance when the hydraulic actuator fails under conditions such as high speed, high temperature, and variable load.

[0007] The present invention is achieved through the following technical solutions.

[0008] The present invention provides a gas turbine fan engine compressor guide vane actuator structure, comprising a connecting pipe head A, a connecting pipe head B, a cavity A, a cavity B, an adjustment component and an action component, wherein the connecting pipe head A is connected to the cavity B, the connecting pipe head B is connected to the cavity A, the adjustment component is connected to the cavity A, the action component is connected to the cavity B, the cavity A and the cavity B are arranged in a shell, and the cavity A is connected to the cavity B.

[0009] Preferably, the adjustment assembly comprises an adjustment screw and a piston, an end face cover is provided on the housing, and the adjustment screw is connected via the end face cover.

[0010] Preferably, a screw hole is provided on the end face cover, the adjusting screw is threadedly connected to the screw hole, the adjusting screw is connected to the piston, the end face cover and the adjusting screw are fixed to the shell through a nut, and the piston is provided in cavity A.

[0011] Preferably, the action component includes a rocker arm, a slider and a rotating shaft. The rocker arm is connected to the piston connecting port through the slider. The rocker arm is arranged in cavity B. One end of the rotating shaft and the end cover are fixed to the shell with the help of a locking assembly. The end cover is connected to the sensor assembly. The connection between the rotating shaft and the rocker arm and the rocker arm pointer is a bite connection.

[0012] Preferably, a connection port is provided at one end of the rotating shaft, the connection port is U-shaped, the rotating shaft is connected to the inner wall of cavity B through a bearing assembly, the rotating shaft is connected to a rocker pointer, and the rocker pointer is provided outside the shell.

[0013] Preferably, a dial is provided on the shell, and the dial is fastened to the shell by bolts A, and the pipe head A is fixedly connected to the cavity B by a pipe joint.

[0014] Preferably, the shell is provided with a hole A, a hole B and a hole C, the hole A and the hole B are provided on both sides of the cavity B, and the pipe connector B includes a P1 end and a P2 end.

[0015] Preferably, an end cover is provided on the shell, and the end cover is provided on one side of the cavity B. The end cover is fastened to the shell through a locking assembly, and the rotating shaft passes through the end cover and is connected to the sensor, and the internal components of the cavity B are closed by the end cover.

[0016] Preferably, a cavity, a connection port and an opening are arranged in the piston, the cavity is arranged on both sides of the piston, and the opening is arranged on both sides of the piston.

[0017] A method for using a compressor guide vane actuator structure of a gas turbine fan engine comprises the following steps: connecting the P1 and P2 ends of a pipe interface B to an engine oil pump control device; when the compressor guide vane adjustment angle needs to be increased, high-pressure oil is introduced into a control chamber at the P1 end of the pipe interface B, and the control chamber at the P2 end of the pipe interface B is communicated with return oil, and a piston rod is pushed under the action of liquid pressure to rotate a rotating shaft, thereby driving the compressor guide vane to move; when the compressor guide vane adjustment angle needs to be reduced, high-pressure oil is introduced into a control chamber at the P2 end of the pipe interface B, and the control chamber at the P1 end of the pipe interface B is communicated with return oil, and a piston rod is pushed under the action of liquid pressure to rotate a rotating shaft, thereby driving the compressor guide vane to move.

[0018] The beneficial effects of the present invention are:

[0019] Compared with the traditional actuator structure, the present invention has a higher functional fault tolerance rate, can effectively provide the hydraulic driving force to drive the compressor guide vane, and feed back the displacement signal of the actuator angle to the engine electronic controller, so that the controller can perform closed-loop control of the compressor guide vane angle; at the same time, it has the function of adjustable mechanical working stroke.

[0020] The control of the present invention has good robustness. The error between the indicated position of the pointer and the actual control accuracy can be adaptively corrected to no more than ±1% according to the adjustment screw, which reflects the good robustness between the RVDT feedback value of the guide vane actuator and the actual angle of the actuator.

[0021] The present invention is easy to install and maintain, adopts an error-proof electrical connector method, fully considers the interchangeability of the product during design, and strives to have a simple structure and easy installation; all interfaces and plug sockets of the product are marked and clearly visible during use and maintenance. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 It is a schematic diagram of the structure of the present invention;

[0023] Figure 2 is a cross-sectional view taken along line AA of the present invention;

[0024] Figure 3 is a BB cross-sectional view of the present invention;

[0025] 1- nut, 2- end face cover, 201- screw hole, 211- connection port, 3- housing, 4- rocker arm pointer, 5- end cover, 6- locking assembly, 7- screw, 8- pipe joint, 9- pipe head A, 10- sensor, 101- connector, 11- hole A, 12- hole B, 13- hole C, 14- adjusting screw, 15- screw 16- dial, 17- pipe head B, 18- piston, 181- cavity, 182- connection port, 183- opening, 19- rocker arm, 20- bearing assembly, 21- rotating shaft, 22- bushing, 23- slider, 24- cavity A, 25- cavity B, 26- fixing pin. DETAILED DESCRIPTION

[0026] The technical solution of the present invention is further described below, but the scope of protection claimed is not limited to the description.

[0027] Example:

[0028] like Figures 1-2 As shown, a gas turbine fan engine compressor guide vane actuator structure includes a connecting pipe A9, a connecting pipe B17, a cavity A24, a cavity B25, an adjusting assembly and an actuating assembly, wherein the connecting pipe A9 is connected to the cavity B25, the connecting pipe B17 is connected to the cavity A24, the adjusting assembly is connected to the cavity A24, the actuating assembly is connected to the cavity B25, the cavity A24 and the cavity B25 are arranged in a shell 3, and the cavity A24 is connected to the cavity B25.

[0029] All connection parts of the actuator structure are threaded, and the screw connection adopts the design of self-locking wire screw sleeve, which fully ensures that the actuator structure will not have the problem of parts falling off under various stress conditions.

[0030] The pipe joint A9, i.e., the P3 end is the lubricating oil output end, which enables the lubricating oil inside the actuator to return to the fuel pump in the form of reflux, forming a lubricating oil circulation loop inside the actuator; the pipe joint B17 is provided with P1 and P2 ends, which are respectively connected to the fuel pump output ends.

[0031] The sensor serves as a receiving end of the actuator signal and is connected to the engine electronic controller to achieve signal reception and feedback.

[0032] The adjustment assembly includes an adjustment screw 14 and a piston 18. An end cap 2 is provided on the housing 3. The adjustment screw 14 is connected to the piston 18 through the end cap 2. A screw hole 201 is provided on the end cap 2. The adjustment screw 14 is threadedly connected to the screw hole 201. The end cap 2 and the adjustment screw 14 are fixed to the housing 3 through a nut 1. The piston 18 is provided in the cavity A24. The internal components of the cavity A24 are sealed by the end cap 2. The adjustment screw 14 is used to adjust the internal space of the cavity 181 at both ends of the piston 18, so as to achieve the adjustment angle driven by the injection oil pressure difference to be consistent with the design value, thereby improving the adjustment accuracy and robustness.

[0033] The action assembly includes a rocker arm 19, a slider 23 and a rotating shaft 21. The rocker arm 19 is connected to the piston connection port 182 through the slider 23. The rocker arm 19 is arranged in the cavity B25. One end of the rotating shaft 21 and the end cover 5 are fixed to the housing 3 by means of a locking assembly 6. The end cover 5 is connected to the sensor 10 assembly. The connection between the rotating shaft 21 and the rocker arm 19 and the rocker arm pointer 4 is a bite connection.

[0034] A connection port 211 is provided at one end of the rotating shaft 21, and the connection port 211 is U-shaped. The connection port 211 is connected to the compressor inlet guide vane adjustment mechanism, and the U-shape enables efficient driving. The rotating shaft 21 is connected to the inner wall of the cavity B25 through the bearing assembly 20, and the rotating shaft 21 is connected to the rocker arm pointer 4, and the rocker arm pointer 4 is arranged on the outside of the shell 3.

[0035] The housing 3 is provided with a dial 16 , which is fastened to the housing 3 by bolts A15 , and the pipe connector A9 is fixedly connected to the cavity B25 by a pipe connector 8 .

[0036] The housing 3 is provided with a hole A11, a hole B12 and a hole C13, the holes A11 and B12 are provided on both sides of the cavity B25, and the pipe head B17 includes a P1 end and a P2 end. The guide vane actuator structure can be assembled and connected with the relevant interface of the aircraft engine; the guide vane actuator is fixed to the outside of the aircraft engine through the hole A11, the hole B12 and the hole C13.

[0037] An end cover 5 is provided on the shell 3, and the end cover 5 is provided on one side of the cavity B25. The end cover 5 is fastened to the shell 3 through a locking assembly 6. The rotating shaft 21 passes through the end cover 5 and is connected to the sensor 10, and the internal components of the cavity B25 are closed by the end cover 5.

[0038] A cavity 181, a connecting port 182 and an opening 183 are provided in the piston 18. The cavity 181 is provided on both sides of the piston 18. The connecting port 182 is engaged and connected with the rocker arm 19 and the slider 23. The opening 183 is provided on both sides of the piston 18 and is connected with the cavity A24 to form the two sides of the oil pressure difference drive of the actuator.

[0039] Several sealing rings are provided at the internal connections of the actuator to achieve flow path sealing. For example, several sealing rings and sealing devices are provided at the contact point between the cavity A24 and the piston 18 to perform lubricating oil sealing to achieve fluid sealing at the flow path position and the contact position. The sealing device can be a sealing ring.

[0040] A method for using a compressor guide vane actuator structure of a gas turbine fan engine comprises the following steps: the P1 and P2 ends of a pipe interface B17 are used as control chamber joint parts of the actuator and are connected to an engine oil pump control device; when the compressor guide vane adjustment angle needs to be increased, high-pressure oil is introduced into the control chamber at the P1 end of the pipe interface B17, and the control chamber at the P2 end of the pipe interface B17 is communicated with the return oil, and the piston rod is pushed under the action of the liquid pressure to rotate the shaft 21, thereby driving the compressor guide vane to move; when the compressor guide vane adjustment angle needs to be reduced, high-pressure oil is introduced into the control chamber at the P2 end of the pipe interface B17, and the control chamber at the P1 end of the pipe interface B17 is communicated with the return oil, and the piston rod is pushed under the action of the liquid pressure to rotate the rotating shaft 21, thereby driving the compressor guide vane to move.

[0041] When the actuator structure is working, the pressure difference between the P1 and P2 ends of the pipe interface B17 drives the piston 18 to move, causing the rocker arm 19 and the rotating shaft 21 to drive the compressor guide vane adjustment mechanism and the rocker arm pointer 4 to indicate the specified adjustment angle value, which can be clearly read through the dial 16; at the same time, the sensor assembly 10 feeds back the actual adjustment angle value to the control system to realize the execution of the closed-loop feedback logic of the adjustment control.

[0042] The invention is applicable to aviation gas turbine fan engines.

Claims

1. A gas turbine fan engine compressor guide vane actuator structure, characterized in that: The invention comprises a pipe connection head A (9), a pipe connection head B (17), a cavity A (24), a cavity B (25), an adjustment component and an action component, wherein the pipe connection head A (9) is connected to the cavity B (25), the pipe connection head B (17) is connected to the cavity A (24), the adjustment component is connected to the cavity A (24), the action component is connected to the cavity B (25), the cavity A (24) and the cavity B (25) are arranged in a shell (3), and the cavity A (24) is connected to the cavity B (25).

2. A gas turbine fan engine compressor guide vane actuator structure as claimed in claim 1, characterized in that: The adjustment assembly comprises an adjustment screw (14) and a piston (18); an end face cover (2) is provided on the housing (3); and the adjustment screw (14) is connected via the end face cover (2).

3. A gas turbine fan engine compressor guide vane actuator structure as claimed in claim 2, characterized in that: The end face cover (2) is provided with a screw hole (201), the adjusting screw (14) is threadedly connected to the screw hole (201), the adjusting screw (14) is connected to the piston (18), the end face cover (2) and the adjusting screw (14) are fixed to the housing (3) via a nut (1), and the piston (18) is arranged in the cavity A (24).

4. A gas turbine fan engine compressor guide vane actuator structure as claimed in claim 1, characterized in that: The action assembly comprises a rocker arm (19), a slider (23) and a rotating shaft (21); the rocker arm (19) is connected to the piston connection port (182) via the slider (23); the rocker arm (19) is arranged in the cavity B (25); one end of the rotating shaft (21) and the end cover (5) are fixed to the housing (3) by means of a locking assembly (6); the end cover (5) is connected to the sensor (10) assembly; the connection between the rotating shaft (21) and the rocker arm (19) and the rocker arm pointer (4) is a bite connection.

5. A gas turbine fan engine compressor guide vane actuator structure as claimed in claim 4, characterized in that: A connection port (211) is provided at one end of the rotating shaft (21), and the connection port (211) is U-shaped. The rotating shaft (21) is connected to the inner wall of the cavity B (25) through a bearing assembly (20). The rotating shaft (21) is connected to a rocker pointer (4), and the rocker pointer (4) is provided outside the housing (3).

6. A gas turbine fan engine compressor guide vane actuator structure as claimed in claim 1, characterized in that: A dial (16) is provided on the housing (3), and the dial (16) is fastened to the housing (3) via bolts A (15). The pipe connector A (9) is fixedly connected to the cavity B (25) via a pipe joint (8).

7. A gas turbine fan engine compressor guide vane actuator structure as claimed in claim 1, characterized in that: The shell (3) is provided with a hole A (11), a hole B (12) and a hole C (13), wherein the hole A (11) and the hole B (12) are arranged on both sides of the cavity B (25), and the pipe connector B (17) includes a P1 end and a P2 end.

8. The gas turbine fan engine compressor guide vane actuator structure according to claim 1, characterized in that: An end cover (5) is arranged on the shell (3), and the end cover (5) is arranged on one side of the cavity B (25). The end cover (5) is fastened to the shell (3) via a locking assembly (6). The rotating shaft (21) passes through the end cover (5) and is connected to the sensor (10), and the internal components of the cavity B (25) are sealed by the end cover (5).

9. A gas turbine fan engine compressor guide vane actuator structure as claimed in claim 2, characterized in that: A cavity (181), a connecting port (182) and an opening (183) are arranged in the piston (18); the cavity (181) is arranged on both sides of the piston (18); and the opening (183) is arranged on both sides of the piston (18).

10. A method for using the compressor guide vane actuator structure of a gas turbine fan engine according to any one of claims 1 to 9, characterized in that: The invention comprises the following steps: connecting the P1 and P2 ends of the pipe interface B (18) to the engine oil pump control device; when the compressor guide vane adjustment angle needs to be increased, high-pressure oil is introduced into the control chamber at the P1 end of the pipe interface B (17); the control chamber at the P2 end of the pipe interface B (17) is communicated with the return oil; under the action of the liquid pressure, the piston rod is pushed to rotate the rotating shaft (21), thereby driving the compressor guide vane to move; when the compressor guide vane adjustment angle needs to be reduced, high-pressure oil is introduced into the control chamber at the P2 end of the pipe interface B (17); the control chamber at the P1 end of the pipe interface B (17) is communicated with the return oil; under the action of the liquid pressure, the piston rod is pushed to rotate the rotating shaft (21), thereby driving the compressor guide vane to move.

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