A directional blasting cutting device for a fan casing containment test blade

Abstract

This application belongs to the technical field of aero-engine containment test, and particularly relates to a device for directional blasting and cutting of fan blade for fan casing containment test. The device includes a cutting cable (1) embedded in a groove of a fan blade (2) to be cut off during flight, and a detonator (3) is connected to an end of the cutting cable (1); a signal receiving device (4) is arranged in a test cabin, an output end of which is connected to the detonator (3) through a detonating lead wire (6), and an input end is connected to a slip ring current collector (7) outside the test cabin through a first lead wire; a Hall sensor (8) is arranged at a predetermined position of a test cabin cover (11) in the test cabin, and is connected to the slip ring current collector (7) through a second lead wire in a cable penetration hole, and is connected to a Hall sensor power supply line (12) located outside the test cabin through a third lead wire; wherein, a magnetic steel bolt (16) for triggering the Hall sensor (8) to work is fixed on the fan blade (2). This application realizes the outward flight of the blade along a predetermined angle.

Description

Technical Field

[0001] The present application belongs to the technical field of aircraft engine containment testing, and specifically relates to a directional blasting and cutting device for fan casing containment testing blades. Background Art

[0002] A prominent safety issue of aircraft engines is the non-containment event of high-speed rotating parts. The working environment of engine blades is harsh, and failure is inevitable. If the casing of a failed high-energy blade is not strong enough, the blade will penetrate the casing and fly out. This situation is called a non-containment event of an aircraft engine. Once the engine is non-contained, it will cause damage to the aircraft, ranging from loss of flight function to aircraft destruction and death. Therefore, military and civilian gas turbine engine specifications around the world all have relevant requirements for containment without exception. Section 33.94 of the "Aircraft Engine Airworthiness Regulations" of my country's civil aviation regulations stipulates: The most dangerous compressor / turbine blade fails at the outermost fixed groove or the integral blade disk must be contained by the casing for at least 80% of the single blade flying outward, and the engine must run for at least 15 seconds without ignition, and its installation node must not fail. This requirement shows that while the airworthiness regulations require the containment of the casing, they also make corresponding requirements for the load-bearing system.

[0003] In the whole-machine containment test, the blades fly out from different angles during the outward flight process, and the impact load on the engine mounting node is not the same. At the same time, the existence of openings (or slots) in the casing structure will also lead to uneven circumferential strength. In order to ensure flight safety, the blades must be controlled to fly out at a predetermined angle to fully assess the casing and the mounting node; at the same time, controlling the blades to fly out at a predetermined angle is also conducive to the high-speed camera to accurately record the blade flying process. At present, domestic and international containment specifications and airworthiness regulations are formulated for aircraft engine whole-machine containment tests. However, conducting containment tests in the whole-machine state is very risky and costly. In order to reduce the test risk and verify the blade flying out technology at a predetermined angle, it is very necessary to conduct a casing containment test with blades flying out at a predetermined angle on a rotor tester.

[0004] In terms of technology, in the existing containment test technology, the blade flies out after reaching the predetermined rotational speed, and the circumferential position where it flies out is random. It cannot ensure that the load on the mounting section is the most severe load, and this assessment is not sufficient, still posing a risk of underassessment. At the same time, due to the randomness of the circumferential position where the blade flies out, multiple high-speed cameras need to be arranged and multiple observation windows need to be added to the test cabin, increasing the difficulty of photography and resulting in a worse containment capacity of the test cabin, affecting test safety. In terms of cost, in the containment test for engine certification, if it cannot be fully proven that the test complies with the regulations in the airworthiness regulations, the test may be repeated, resulting in huge economic cost consumption. In the existing technical solutions, multiple cameras need to be purchased, increasing the test cost. In terms of efficiency, due to the randomness of the circumferential position where the blade flies out in the containment test, multiple cameras need to be arranged and jointly debugged, resulting in a low test efficiency. Summary of the Invention

[0005] To solve the above problems, the present application provides a device for directional blasting cutting of blades in a fan casing containment test, ensuring that the blades break and fly out at a predetermined angle.

[0006] The device for directional blasting cutting of blades in the fan casing containment test of the present application mainly includes:

[0007] Cutting cables, embedded in the grooves of the fan blades to be broken, and detonators are connected to the ends of the cutting cables;

[0008] Signal receiving device, arranged in the test cabin, the output end of the signal receiving device is connected to the detonator through a detonating lead, and the input end of the signal receiving device is connected to a slip ring electrical connector outside the test cabin through a first lead;

[0009] Hall sensors, arranged at predetermined positions on the test cabin cover in the test cabin, and connected to the slip ring electrical connector through a second lead in the through-cabin hole. At the same time, it is connected to the Hall sensor power supply line outside the test cabin through a third lead in the through-cabin hole;

[0010] Among them, a magnetic steel bolt for triggering the operation of the Hall sensor is fixed on the fan blade, and the predetermined position refers to the position where it is expected that the fan blade breaks when rotating to a specific circumferential position, and this specific circumferential position corresponds to the position of the test cabin cover.

[0011] Preferably, there are two cutting cables, which are respectively arranged in the back blade grooves and the front blade grooves of the blade, and the two cutting cables are connected to the same detonator.

[0012] Preferably, the signal receiving device is installed on one end of the drive shaft of the fan blade located inside the test chamber, the slip ring current collector is installed on the other end of the drive shaft of the fan blade located outside the test chamber, the drive shaft is a hollow shaft with a central through hole, and the first lead extends in the central through hole of the drive shaft.

[0013] Preferably, the slip ring current collector is fixed to the end of the drive shaft through a current collector mounting seat.

[0014] Preferably, the central through hole of the drive shaft is sealed with resin glue at the end located outside the test chamber.

[0015] Preferably, the detonating lead is arranged closely against the fan disk of the fan blade and is connected to the signal receiving device after passing through the lead hole provided on the fan disk.

[0016] Preferably, the Hall sensor is fixed to the test chamber cover through a Hall sensor mounting bracket.

[0017] Preferably, a seal is provided at one end of the cable penetration hole close to the outside of the test chamber. The seal includes a sealing bolt and a conical silicone gasket. The cable penetration hole has a stop at the side facing the outside of the test chamber. The bottom surface of the conical silicone gasket is located at the stop, and the top surface of the conical silicone gasket is a conical surface. When the sealing bolt is screwed into the cable penetration hole, it can squeeze the conical surface of the conical silicone gasket.

[0018] Preferably, the fan blade is weighted by removing part of the structure of the fan disk mounting edge at the position where the magnetic steel bolt is installed.

[0019] Preferably, the predetermined position includes the position where it is desired that the fan blade breaks off when rotating to a specific circumferential position, which is a position in front of the position of the test chamber cover directly above this specific circumferential position. The term "in front" refers to the direction of rotation of the fan blade.

[0020] This application solves the problem of controlling the flying angle of the blade and realizes the blade flying outwards at a predetermined angle. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 is a schematic diagram of constant-speed and directional blasting cutting of a preferred embodiment of the fan casing containment test blade directional blasting cutting device of this application.

[0022] Figure 2 is this application Figure 1 Schematic diagram of the cable penetration lead seal of the shown embodiment.

[0023] Among them, 1 - cutting cable, 2 - fan blade, 3 - detonator, 4 - signal receiving device, 5 - drive shaft, 6 - detonating lead wire, 7 - slip ring electrical connector, 8 - Hall sensor, 9 - electrical connector mounting seat, 10 - resin glue, 11 - test cabin cover, 12 - Hall sensor power supply line, 13 - Hall sensor mounting bracket, 14 - sealing bolt, 15 - conical silicone gasket, 16 - magnetic steel bolt, 17 - fan disc, 18 - lead wire hole. Detailed implementation manners

[0024] To make the purpose, technical solutions and advantages of the implementation of this application clearer, the technical solutions in the implementation manners of this application will be described in more detail below with reference to the accompanying drawings in the implementation manners of this application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements with the same or similar functions from beginning to end. The described implementation manners are part of the implementation manners of this application, rather than all of the implementation manners. The implementation manners described below by referring to the accompanying drawings are exemplary and are intended to explain this application, and should not be construed as a limitation to this application. Based on the implementation manners in this application, all other implementation manners obtained by those of ordinary skill in the art without creative efforts belong to the scope of protection of this application. The implementation manners of this application will be described in detail below with reference to the accompanying drawings.

[0025] This application provides a directional blasting cutting device for a fan casing to contain test blades, as Figure 1 shown, mainly including:

[0026] The cutting cable 1 is embedded in the groove of the fan blade 2 to be cut off during flight, and the end of the cutting cable 1 is connected with a detonator 3;

[0027] The signal receiving device 4 is arranged in the test cabin. The output end of the signal receiving device 4 is connected to the detonator 3 through the detonating lead wire 6, and the input end of the signal receiving device 4 is connected to the slip ring electrical connector 7 outside the test cabin through a first lead wire;

[0028] The Hall sensor 8 is arranged at a predetermined position of the test cabin cover 11 in the test cabin, and is connected to the slip ring electrical connector 7 through a second lead wire in the through-cabin hole. At the same time, it is connected to the Hall sensor power supply line 12 located outside the test cabin through a third lead wire in the through-cabin hole;

[0029] Among them, a magnetic steel bolt 16 for triggering the Hall sensor 8 to work is fixed on the fan blade 2, and the predetermined position refers to the position where it is expected that the fan blade 2 will be cut off when it rotates to a specific circumferential position, and this specific circumferential position is the position of the test cabin cover directly opposite.

[0030] The present application proposes a blade constant-speed and directional blasting cutting device, which generates a trigger signal through a Hall sensor to detonate a cutting cable embedded in the blade groove, so as to make the blade fly out along a predetermined circumferential position at a predetermined rotational speed. Among them, during the containment test, when the rotor speed reaches the predetermined speed, the power supply circuit 12 of the Hall sensor is closed to supply power to the Hall sensor 8; when the fan blade reaches the circumferential position where the Hall sensor 8 is located, the magnetic steel bolt 16 sweeps across the Hall sensor 8, and under the action of electromagnetic induction, the Hall sensor 8 generates a pulse signal, which is transmitted to the signal receiving device 4 through the slip ring current collector 7; after receiving the pulse trigger signal, the signal receiving device 4 sends a detonating signal to the detonator 3, and after the detonator 3 is triggered, it detonates the cutting cable 1 to cut off the fan blade 2, so that the fan blade 2 flies out along the predetermined circumferential position.

[0031] In some alternative embodiments, the cutting cable 1 includes two, which are respectively arranged in the back groove and the front groove of the blade, and the two cutting cables 1 are connected to the same detonator 3. In the present application, the cutting cables are respectively arranged on both sides of the blade, which improves the cutting success rate.

[0032] In some alternative embodiments, the signal receiving device 4 is installed on one end of the drive shaft 5 of the fan blade located inside the test chamber, the slip ring current collector 7 is installed on the other end of the drive shaft 5 of the fan blade located outside the test chamber, the drive shaft 5 is a hollow shaft with a central through hole, and the first lead wire extends in the central through hole of the drive shaft 5.

[0033] In some alternative embodiments, the slip ring current collector 7 is fixed to the end of the drive shaft through the current collector mounting seat 9.

[0034] In some alternative embodiments, the central through hole of the drive shaft 5 is blocked by a resin adhesive 10 at the end located outside the test chamber. In the present application, at the position where the Hall sensor lead wire enters the top end of the hollow drive shaft, the inner hole of the hollow drive shaft is blocked by a resin adhesive to prevent air from entering the vacuum test chamber.

[0035] In some alternative embodiments, the detonating lead wire 6 is arranged closely to the fan disc 17 of the fan blade, and is connected to the signal receiving device 4 after passing through the lead wire hole 18 provided on the fan disc 17. In this embodiment, the detonating lead wire of the detonator is led inward to the signal receiving device successively through the wheel disc tenon groove, the front end face, the journal lead wire hole, and the rotor drive shaft lead wire hole, and the lead wire is fixed by a resin adhesive.

[0036] In some alternative embodiments, the Hall sensor 8 is fixed to the test chamber cover 11 through the Hall sensor mounting bracket 13. In this embodiment, a Hall sensor bracket is installed on the test chamber cover in the predetermined flying direction of the blade, the bracket is fixed to the test chamber cover by bolts, and the Hall sensor is fixed to the bracket by a lock nut.

[0037] In some alternative embodiments, a seal is provided at one end of the cable penetration hole close to the outside of the test chamber. The seal includes a sealing bolt 14 and a conical silicone gasket 15. The cable penetration hole has a stop on the side facing the outside of the test chamber. The bottom surface of the conical silicone gasket 15 is located at the stop, and the top surface of the conical silicone gasket 15 is a conical surface. When the sealing bolt 14 is screwed into the cable penetration hole, it can squeeze the conical surface of the conical silicone gasket 15.

[0038] Reference Figure 2 , in this embodiment, when the lead wire of the Hall sensor passes through the vacuum chamber cover, a dedicated cable penetration sealing structure is designed. A conical silicone gasket is placed in the lead wire hole of the test chamber cover. After the cable passes through the hole, the sealing bolt is tightened. After the silicone gasket is squeezed, it clamps the sensor lead wire to achieve the sealing of the chamber body.

[0039] In some alternative embodiments, the fan blade 2 is balanced by removing part of the structure of the fan disk mounting edge at the position where the magnet bolt 16 is installed. Reference Figure 1 , after drilling through holes on the fan disk mounting edge corresponding to the circumferential position of the fan blade 2 and opposite to the Hall sensor position where the blade is to be broken off, since the installation of the magnet material bolt causes unbalanced mass, it is necessary to remove the weight by cutting off part of the structure on the mounting edge to balance the unbalance caused by the magnet bolt.

[0040] In some alternative embodiments, the predetermined position includes a position where it is desired that the fan blade 2 breaks off when it rotates to a specific circumferential position, and this position is in front of the position of the test chamber cover directly above this specific circumferential position. The term "in front" refers to the direction of rotation of the fan blade.

[0041] It can be understood that this application expects the fan blade to break off at a specific circumferential position. Therefore, in technical implementation, a Hall sensor is provided on the test chamber cover corresponding to this specific circumferential position of the fan blade, so that after the fan blade rotates to this specific circumferential position, a blasting signal is triggered to cut off the blade. However, considering the time delay of signal transmission and the high rotational speed characteristics of the fan blade, when it is desired that the blade breaks off at a specific position, the Hall sensor needs to be arranged at some positions in front, that is, the predetermined position is set forward. In this way, after superimposing the time of signal transmission, it can be ensured that the fan blade breaks off at a specific circumferential position. The specific parameters for setting forward can be determined through experiments.

[0042] Compared with the prior art, the main advantages of this application are as follows:

[0043] 1. In the existing test technology, the circumferential angle at which the blade flies out is random. This application solves the problem of controlling the flying-out angle of the blade and realizes that the blade flies outwards along a predetermined angle;

[0044] 2. This application solves the installation problem of the directional initiation flying cut-off device;

[0045] 3. This application solves the problem of the cabin sealing during the signal line extraction process;

[0046] 4. This application solves the problem of the directional trigger signal transmission between the rotor and stator, ensuring the safe and reliable operation of the initiation system;

[0047] 5. This application only needs to arrange a camera at a fixed circumferential position, significantly saving the test cost.

[0048] Although the present application has been described in detail with general descriptions and specific implementation manners in the foregoing text, based on the present application, some modifications or improvements can be made, which are obvious to those skilled in the art. Therefore, these modifications or improvements made without departing from the spirit of the present application all fall within the scope claimed by the present application.

Claims

1. A directional blasting cutting device for a fan casing containment test blade, characterized in that, Comprising: A cutting cable (1) embedded in a groove of a fan blade (2) to be flown off, and a detonator (3) is connected to an end of the cutting cable (1); A signal receiving device (4) is arranged in the test cabin, an output end of the signal receiving device (4) is connected to the detonator (3) through a detonating lead (6), and an input end of the signal receiving device (4) is connected to a slip ring electrical connector (7) outside the test cabin through a first lead; A Hall sensor (8) is arranged at a predetermined position of a test cabin cover (11) in the test cabin, and is connected to the slip ring electrical connector (7) through a second lead in a through-cabin hole. Meanwhile, it is connected to a Hall sensor power supply line (12) located outside the test cabin through a third lead in the through-cabin hole; Wherein, a magnetic steel bolt (16) for triggering the Hall sensor (8) to work is fixed on the fan blade (2), and the predetermined position refers to the position of the test cabin cover opposite to the specific circumferential position where it is expected that the fan blade (2) will be flown off when rotating to a specific circumferential position.

2. The fan casing containment test blade directional blasting and cutting device according to claim 1, wherein, There are two cutting cables (1), which are respectively arranged in the back blade groove and the front blade groove of the blade, and the two cutting cables (1) are connected to the same detonator (3).

3. The fan casing containment test blade directional blasting and cutting device according to claim 1, wherein, The signal receiving device (4) is installed on one end of a drive shaft (5) of the fan blade located in the test cabin, the slip ring electrical connector (7) is installed on the other end of the drive shaft (5) of the fan blade located outside the test cabin, the drive shaft (5) is a hollow shaft with a central through hole, and the first lead extends in the central through hole of the drive shaft (5).

4. The fan casing containment test blade directional blasting and cutting device according to claim 3, wherein The slip ring electrical connector (7) is fixed to the drive shaft end through an electrical connector mounting seat (9).

5. The fan casing containment test blade directional blasting and cutting device according to claim 3, characterized in that, The central through hole of the drive shaft (5) is sealed with resin glue (10) at the end located outside the test cabin.

6. The fan casing containment test blade directional blasting cutting device according to claim 3, characterized in that, The detonating lead (6) is arranged close to a fan disc (17) of the fan blade, and is connected to the signal receiving device (4) after passing through a lead hole (18) provided on the fan disc (17).

7. The fan casing containment test blade directional blasting and cutting device according to claim 1, characterized in that, The Hall sensor (8) is fixed to the test cabin cover (11) through a Hall sensor mounting bracket (13).

8. The fan casing containment test blade directional blasting and cutting device according to claim 1, wherein, A sealing member is provided at one end of the through-cabin hole close to the outside of the test cabin. The sealing member includes a sealing bolt (14) and a conical silicone gasket (15). The through-cabin hole has a stop at the side facing the outside of the test cabin. The bottom surface of the conical silicone gasket (15) is located at the stop, and the top surface of the conical silicone gasket (15) is a conical surface. When the sealing bolt (14) is screwed into the through-cabin hole, the conical surface of the conical silicone gasket (15) can be squeezed.

9. The fan casing containment test blade directional blasting cutting device according to claim 1, wherein, The fan blade (2) is de-weighted by removing part of the structure of the fan disc mounting edge at the position where the magnetic steel bolt (16) is installed.

10. The fan casing containment test blade directional blasting cutting device according to claim 1, characterized in that, The predetermined position includes the position in front of the position of the test cabin cover directly above the specific circumferential position where it is expected that the fan blade (2) will be flown off when rotating to a specific circumferential position. The "front" refers to the direction of rotation of the fan blade.

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