Aero-generator thermal trip mechanism

Abstract

The application belongs to the technical field of aero-generator thermal trip mechanism design, and particularly relates to an aero-generator thermal trip mechanism, which can be supported on an aero-generator shell through screw connection in specific application, and the shell can be connected to an aero-generator end cover through a flange. When starting to work, the aero-generator thermal trip mechanism is in a preset state, so that the aero-generator can work normally. When the temperature in the aero-generator exceeds a set threshold, the aero-generator thermal trip mechanism is automatically switched to a tripping state, so that the aero-generator stops working. In the process, the switching shaft and the aero-generator driving shaft are disconnected from the aero-generator input shaft mainly by screw transmission, so that the aero-generator thermal trip mechanism has high reliability, timely tripping and small risk.

Description

Technical Field

[0001] This application belongs to the technical field of thermal trip mechanism design for aircraft generators, and specifically relates to a thermal trip mechanism for aircraft generators. Background Technology

[0002] The aircraft engine input shaft is connected to the flight attachment box drive shaft, and operates by being driven by the flight attachment box drive shaft.

[0003] When the cooling system of an aircraft engine malfunctions, or when there are problems such as oil churning or rotor rubbing, the internal temperature of the aircraft generator will rise rapidly. If the aircraft generator continues to operate when the internal temperature exceeds 200°C, the malfunction will be further aggravated, and even a fire may occur. Therefore, a thermal trip mechanism is designed to disconnect the aircraft engine input shaft from the aircraft generator drive shaft when the internal temperature of the aircraft generator exceeds the set temperature, so that the aircraft generator gradually stops working and can be repaired.

[0004] Currently, the thermal release mechanism of aero-engines is a low-melting-point alloy thermal release, which relies entirely on the spring force to overcome friction and disengage the aero-engine input shaft from the aero-generator drive shaft. Due to uneven heating of the low-melting-point alloy and defects in spring processing, the disengagement efficiency of the aero-engine input shaft from the aero-generator drive shaft is low, the reliability is low, and there is a significant risk that the disengagement may not be timely.

[0005] This application is made in view of the aforementioned technical deficiencies.

[0006] It should be noted that the above background information is only used to assist in understanding the inventive concept and technical solution of this application, and it does not necessarily belong to the prior art of this patent application. In the absence of clear evidence that the above information was disclosed on the filing date of this application, the above background information should not be used to evaluate the novelty and inventiveness of this application. Summary of the Invention

[0007] The purpose of this application is to provide a thermal trip mechanism for an aircraft generator to overcome or mitigate at least one of the known technical defects.

[0008] The technical solution of this application is:

[0009] A thermal trip mechanism for an aircraft generator, comprising:

[0010] A support base with a support hole and an anti-rotation notch in the support hole;

[0011] The pull rod has a through-support hole and has an anti-rotation groove, a first annular protrusion and a first guide groove on its side wall. One end of the rod has a first insertion hole; the first insertion hole connects to the first guide groove.

[0012] Anti-rotation pins are installed in anti-rotation notches and anti-rotation grooves;

[0013] The worm shaft has a positioning hole on its side wall, a trapezoidal thread at one end, and the other end is inserted into the first insertion hole. The side wall of the other end has a first pin hole and a second annular protrusion.

[0014] The first connecting pin is provided in the first pin hole and the first guide groove;

[0015] The first spring is sleeved on the outer circumference of the pull rod, and its two ends are connected between the support seat and the first annular protrusion.

[0016] The second spring is sleeved on the outer periphery of the first spring, with both ends connected between the support base and the second annular protrusion;

[0017] shell;

[0018] The coil, housed inside the casing, is connected to the controller via wires extending from the casing; the controller acquires the internal temperature of the aircraft generator through sensors.

[0019] The iron core is set inside the coil and has mounting holes.

[0020] An armature is installed inside a mounting hole, with its head extending out of the outer casing;

[0021] The third spring is installed in the mounting hole and connected between the bottom of the mounting hole and the bottom of the armature;

[0022] The aircraft generator drive shaft has a second guide groove on its side wall and a second insertion hole at its end; the second insertion hole communicates with the second guide groove.

[0023] The adapter shaft is installed in the second insertion hole, has a second pin hole on its side wall, has an end face tooth on its outward end, and has a spline fit between the outer wall of its inward end and the side wall of the second insertion hole.

[0024] A sliding sleeve is fitted around the outer periphery of the aircraft generator drive shaft, and its sidewall has a third pin hole and a trapezoidal thread.

[0025] The second connecting pin is provided in the second guide groove, the second pin hole, and the third pin hole;

[0026] The fourth spring is installed inside the second insertion hole and is connected between the bottom of the second insertion hole and one end of the adapter shaft.

[0027] The input shaft of the aircraft generator has an output end that extends into the second insertion hole and has end face teeth at the end.

[0028] The thermal trip mechanism of an aircraft generator has the following features:

[0029] In the preset state, when the internal temperature of the aircraft generator is lower than the set threshold, the controller control coil is de-energized, and the armature is subjected to the elastic force of the third spring, so that the head is inserted into the positioning hole, keeping the trapezoidal thread on the worm shaft disengaged from the trapezoidal thread on the sliding sleeve. Under the elastic force of the fourth spring, the upper end face teeth of the adapter shaft mesh with the upper end face teeth of the aircraft generator input shaft. At this time, the aircraft generator input shaft can drive the aircraft generator drive shaft to rotate through the adapter shaft, so that the aircraft generator works.

[0030] In the tripped state, when the internal temperature of the aircraft generator exceeds the set threshold, the controller control coil is energized, generating magnetic force through the iron core. This causes the armature to overcome the elastic force of the third spring and move, disengaging the head from the positioning hole. This causes the pull rod and worm shaft to move under the elastic force of the first and second springs, engaging the trapezoidal thread on the worm shaft with the trapezoidal thread on the sliding sleeve. The sliding sleeve, driven by the adapter shaft and the aircraft generator drive shaft via the second connecting pin, rotates and slides along the axial direction of the aircraft generator drive shaft under the action of the trapezoidal thread. The second connecting pin then drives the adapter shaft to move, causing the upper end face teeth of the adapter shaft to disengage from the upper end face teeth of the aircraft generator input shaft, thereby stopping the aircraft generator drive shaft from rotating and stopping the aircraft generator from working.

[0031] According to at least one embodiment of this application, in the above-described aircraft generator thermal release mechanism, the support base has a first positioning hole, and the first spring is engaged in the first positioning hole;

[0032] The support base has a second positioning hole, and the second spring is engaged in the second positioning hole;

[0033] The bottom of the mounting hole has a third positioning hole, and the third spring is locked in the third positioning hole;

[0034] The inner end of the adapter shaft has a fourth positioning hole, and the fourth spring is locked in the fourth positioning hole.

[0035] According to at least one embodiment of this application, in the above-mentioned thermal trip mechanism of the aircraft generator, the iron core is welded from three sections, the middle section is made of non-magnetic material, the mounting hole is formed on the front section and the middle section, and the third spring is located between the rear section and the bottom of the armature.

[0036] When the thermal trip mechanism of the aircraft generator is in the tripped state, the iron core at the rear end is in conical contact with the bottom of the armature.

[0037] According to at least one embodiment of this application, in the above-described aircraft generator thermal trip mechanism, the output end of the aircraft generator input shaft is mounted in the second insertion hole via a bearing.

[0038] According to at least one embodiment of this application, in the above-described aircraft generator thermal release mechanism, the side wall of the end of the pull rod facing away from the worm shaft has a connecting through hole;

[0039] The thermal trip mechanism for aircraft generators also includes:

[0040] The pull ring is engaged in the connecting through hole.

[0041] According to at least one embodiment of this application, the above-described aircraft generator thermal trip mechanism further includes:

[0042] The bushing is fitted onto the outer circumference of the worm shaft, and its outer wall has an annular edge; the annular edge is placed between the second spring and the second annular protrusion.

[0043] This application has at least the following beneficial technical effects:

[0044] A thermal trip mechanism for an aircraft generator is provided. In practical applications, its support base can be connected to the aircraft generator housing with screws, and the housing can be connected to the aircraft generator end cover via a flange. When the aircraft generator starts working, the thermal trip mechanism is configured in a preset state to ensure that the aircraft generator can work normally. When the temperature inside the aircraft generator exceeds a set threshold, specifically exceeding 200°C, it automatically switches to the trip state to stop the aircraft generator from working. In this process, the adapter shaft and its aircraft generator drive shaft are mainly separated from the aircraft generator input shaft by threaded transmission. It has high reliability, timely tripping, and low risk. It has been verified that the tripping can be completed within 1 second. Attached Figure Description

[0045] Figure 1 This is a schematic diagram of the thermal trip mechanism of the aircraft generator provided in this application embodiment in a preset state;

[0046] Figure 2 This is a schematic diagram of the thermal trip mechanism of the aircraft generator provided in this application embodiment in the tripped state;

[0047] Figures 3-5 This is a partial schematic diagram of the thermal trip mechanism for an aircraft generator provided in an embodiment of this application;

[0048] in:

[0049] 1-Worm shaft; 2-Pull rod; 3-Bushing; 4-Second spring; 5-First connecting pin; 6-First spring; 7-Support seat; 8-Pull ring; 9-Anti-rotation pin; 10-Armature; 11-Iron core; 12-Coil; 13-Third spring; 14-Outer shell; 15-Sliding sleeve; 16-Fourth spring; 17-Aircraft generator input shaft; 18-Adapter shaft; 19-Aircraft generator drive shaft; 20-Second connecting pin.

[0050] To better illustrate this embodiment, some parts in the accompanying drawings may be omitted, enlarged, or reduced, and do not represent the actual size of the product. Furthermore, the accompanying drawings are for illustrative purposes only and should not be construed as limiting this patent. Detailed Implementation

[0051] To make the technical solution and advantages of this application clearer, the technical solution of this application will be described in a clearer and more complete manner below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are only some embodiments of this application, and are only used to explain this application, not to limit this application. It should be noted that, for ease of description, only the parts related to this application are shown in the accompanying drawings. Other related parts can be referred to the general design. In the absence of conflict, the embodiments and technical features in the embodiments of this application can be combined with each other to obtain new embodiments.

[0052] Furthermore, unless otherwise defined, the technical or scientific terms used in this application description shall have the ordinary meaning understood by one of ordinary skill in the art to which this application pertains. The terms "upper," "lower," "left," "right," "center," "vertical," "horizontal," "inner," and "outer," etc., used in this application description to indicate relative direction or positional relationship are used only to indicate relative orientation or positional relationship, and do not imply that the device or component must have a specific orientation, or be constructed and operated in a specific orientation. When the absolute position of the described object changes, its relative positional relationship may also change accordingly, and therefore should not be construed as a limitation on this application. The terms "first," "second," "third," and similar terms used in this application description are used only for descriptive purposes to distinguish different components, and should not be construed as indicating or implying relative importance. The terms "a," "one," or "the," etc., used in this application description should not be construed as an absolute limitation on quantity, but should be construed as indicating the existence of at least one. The terms "including," "comprising," etc., used in this application description mean that the element or object preceding the word covers the element or object listed after the word and its equivalents, without excluding other elements or objects.

[0053] Furthermore, it should be noted that, unless otherwise explicitly specified and limited, terms such as “installation,” “connection,” and “linkage” used in the description of this application should be interpreted broadly. For example, a connection can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium; it can also refer to the internal connection of a component. Those skilled in the art can understand its specific meaning in this application according to the specific circumstances.

[0054] The following is in conjunction with the appendix Figures 1 to 5 This application will be described in further detail.

[0055] A thermal trip mechanism for an aircraft generator, comprising:

[0056] Support base 7, which has a support hole and an anti-rotation notch in the support hole;

[0057] The pull rod 2 is provided through the support hole, and has an anti-rotation groove, a first annular protrusion and a first guide groove on its side wall. One end has a first insertion hole; the first insertion hole is connected to the first guide groove.

[0058] Anti-rotation pin 9 is installed in the anti-rotation notch and anti-rotation groove;

[0059] The worm shaft 1 has a positioning hole on its side wall, a trapezoidal thread at one end, and is inserted into a first insertion hole at the other end. The side wall of this end has a first pin hole and a second annular protrusion.

[0060] The first connecting pin 5 is provided in the first pin hole and the first guide groove;

[0061] The first spring 6 is sleeved on the outer periphery of the pull rod 2, and its two ends are connected between the support base 7 and the first annular protrusion.

[0062] The second spring 4 is sleeved on the outer periphery of the first spring 6, and its two ends are connected between the support base 7 and the second annular protrusion.

[0063] 14 for the outer casing;

[0064] Coil 12 is installed inside housing 14 and connected to controller via wires passing through housing 14; controller collects the temperature inside aircraft generator via sensor;

[0065] The iron core 11 is disposed inside the coil 12 and has mounting holes thereon;

[0066] An armature 10 is installed in a mounting hole, with its head extending out of the outer casing 14;

[0067] The third spring 13 is installed in the mounting hole and connected between the bottom of the mounting hole and the bottom of the armature 10;

[0068] The aircraft generator drive shaft 19 has a second guide groove on its side wall and a second insertion hole at its end; the second insertion hole communicates with the second guide groove.

[0069] The adapter shaft 18 is installed in the second insertion hole, has a second pin hole on its side wall, has an end face tooth on its outward end, and has a spline fit between the outer wall of its inward end and the side wall of the second insertion hole.

[0070] Sliding sleeve 15 is fitted around the outer periphery of the aircraft generator drive shaft 19, and its sidewall has a third pin hole and a trapezoidal thread.

[0071] The second connecting pin 20 is provided in the second guide groove, the second pin hole, and the third pin hole;

[0072] The fourth spring 16 is installed inside the second insertion hole and is connected between the bottom of the second insertion hole and the inward end of the adapter shaft 18.

[0073] The aircraft generator input shaft 17 has an input end connected to the flight attachment housing drive shaft and an output end extending into the second insertion hole, with end face teeth at the end.

[0074] The thermal trip mechanism of an aircraft generator has the following features:

[0075] In the preset state, when the internal temperature of the aircraft generator is below a set threshold, the controller control coil 12 is de-energized. The armature 10, under the elastic force of the third spring 13, inserts its head into the positioning hole, keeping the trapezoidal thread on the worm shaft 1 disengaged from the trapezoidal thread on the sliding sleeve 15. Under the elastic force of the fourth spring 16, the upper end face teeth of the adapter shaft 18 mesh with the upper end face teeth of the aircraft generator input shaft 17. At this time, the aircraft generator input shaft 17 can drive the aircraft generator drive shaft 19 to rotate via the adapter shaft 18, thus enabling the aircraft generator to operate. Figure 1 As shown;

[0076] In the tripped state, when the internal temperature of the aircraft generator exceeds the set threshold, the controller control coil 12 is energized, generating magnetic force through the iron core 11. This causes the armature 10 to move against the elastic force of the third spring 13, disengaging its head from the positioning hole. This causes the pull rod 2 and worm shaft 1 to move under the elastic force of the first spring 6 and the second spring 4, respectively. This engages the trapezoidal thread on the worm shaft 1 with the trapezoidal thread on the sliding sleeve 15. The sliding sleeve 15 is driven to rotate by the adapter shaft 18 and the aircraft generator drive shaft 19 via the second connecting pin 20. Under the action of the trapezoidal thread, it slides along the axial direction of the aircraft generator drive shaft 19, driving the adapter shaft 18 to move via the second connecting pin 20. This causes the upper end face teeth of the adapter shaft 18 to disengage from the upper end face teeth of the aircraft generator input shaft 17, thereby stopping the rotation of the aircraft generator drive shaft 19 and stopping the aircraft generator from operating. Figure 2 As shown.

[0077] In specific applications, the thermal trip mechanism of the aircraft generator disclosed in the above embodiments can have its support base 7 connected to the aircraft generator housing by screws, and the outer casing 14 connected to the aircraft generator end cover by flanges. When the aircraft generator starts working, the thermal trip mechanism is configured in a preset state to ensure that the aircraft generator can work normally. When the temperature inside the aircraft generator exceeds a set threshold, specifically exceeding 200°C, it automatically switches to the trip state to stop the aircraft generator from working. In this process, the adapter shaft 18 and its aircraft generator drive shaft 19 are mainly separated from the aircraft generator input shaft 17 by threaded transmission. It has high reliability, timely tripping, and low risk. It has been verified that the tripping can be completed within 1 second.

[0078] The thermal trip mechanism of the aircraft generator disclosed in the above embodiment requires timely maintenance of the aircraft generator after tripping. After maintenance, the pull rod 2 can be pulled away from the end of the worm shaft 1, causing the pull rod 2 and the worm shaft 1 to move against the elastic force of the first spring 6 and the second spring 4, thus resetting the mechanism. This keeps the trapezoidal thread on the worm shaft 1 disengaged from the trapezoidal thread on the sliding sleeve 15, allowing the adapter shaft 18 to slide axially along the aircraft generator drive shaft 19 under the elastic force of the fourth spring 16. The second connecting pin 20 drives the sliding sleeve 15 to move, causing the upper end face teeth of the adapter shaft 18 to mesh with the upper end face teeth of the aircraft generator input shaft 17. At this time, the temperature inside the aircraft generator is below the preset threshold, the controller control coil 12 is de-energized, and the armature 10 is inserted into the positioning hole under the elastic force of the third spring 13, returning the aircraft generator thermal trip mechanism to the preset state, waiting for the next time the temperature inside the aircraft generator exceeds the set threshold to activate.

[0079] In some optional embodiments, in the above-described aircraft generator thermal release mechanism, the support base 7 has a first positioning hole, and the first spring 6 is engaged in the first positioning hole;

[0080] The support base 7 has a second positioning hole, and the second spring 4 is engaged in the second positioning hole;

[0081] The bottom of the mounting hole has a third positioning hole, and the third spring 13 is locked in the third positioning hole;

[0082] The inner end of the adapter shaft 18 has a fourth positioning hole, and the fourth spring 16 is engaged in the fourth positioning hole.

[0083] In some optional embodiments, in the above-mentioned thermal trip mechanism of the aircraft generator, the iron core 11 is welded from three sections, the middle section is made of non-magnetic material, and the mounting hole is formed on the front section and the middle section, so that the magnetic circuit closes from the armature 10, reducing magnetic leakage and increasing electromagnetic force. The third spring 13 is located between the rear section and the bottom of the armature 10.

[0084] When the thermal trip mechanism of the aircraft generator is in the tripped state, the iron core 11 at the rear end makes contact with the bottom of the armature 10 through a conical surface, increasing the force-bearing area and thus increasing the electromagnetic attraction of the electromagnet.

[0085] In some alternative embodiments, in the above-described thermal trip mechanism for the aircraft generator, the output end of the aircraft generator input shaft 17 is mounted in the second insertion hole via a bearing.

[0086] In some optional embodiments, in the above-described aircraft generator thermal release mechanism, the side wall of the pull rod 2 facing away from the worm shaft 1 has a connecting through hole;

[0087] The thermal trip mechanism for aircraft generators also includes:

[0088] Pull ring 8 is engaged in the connecting through hole, and pull rod 2 can be pulled through pull ring 8.

[0089] In some optional embodiments, the above-described aircraft generator thermal trip mechanism further includes:

[0090] Bushing 3 is fitted around the outer circumference of worm shaft 1, and its outer wall has an annular edge; the annular edge is placed between the second spring 4 and the second annular protrusion.

[0091] In some alternative embodiments, in the above-described aircraft generator thermal trip mechanism, the components can be centered and positioned by means of a stop fit.

[0092] The various embodiments in the specification are described in a progressive manner, with each embodiment focusing on the differences from other embodiments. The same or similar parts between the various embodiments can be referred to each other.

[0093] The technical solution of this application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of this application is obviously not limited to these specific embodiments. Without departing from the principles of this application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will all fall within the scope of protection of this application.

Claims

1. A thermal trip mechanism for an aircraft generator, characterized in that, include: Support base (7), which has support holes; The worm shaft (1) is set in the support hole, with a positioning hole and a second annular protrusion on the side wall, and a trapezoidal thread at one end. The second spring (4) is connected between the support base (7) and the second annular protrusion; Outer shell (14); A coil (12) is installed inside a housing (14) and connected to a controller; An iron core (11) is disposed inside a coil (12) and has mounting holes thereon; An armature (10) is installed in the mounting hole; The third spring (13) is connected between the bottom of the mounting hole and the bottom of the armature (10); The aircraft generator drive shaft (19) has a second guide groove on its side wall and a second insertion hole at its end; The adapter shaft (18) is provided in the second insertion hole, has a second pin hole on the side wall, and has an end face tooth on the outward end; The sliding sleeve (15) is fitted on the outer periphery of the aircraft generator drive shaft (19), and the side wall has a third pin hole and a trapezoidal thread; The second connecting pin (20) is provided in the second guide groove, the second pin hole, and the third pin hole; The fourth spring (16) is connected between the bottom of the second insertion hole and the inward end of the adapter shaft (18); The input shaft (17) of the aircraft generator extends into the second insertion hole at the output end, and has end face teeth at the end. The thermal trip mechanism of an aircraft generator has the following features: In the preset state, the temperature inside the aircraft generator is lower than the set threshold, the controller control coil (12) is de-energized, the armature (10) is subjected to the elastic force of the third spring (13), the head is inserted into the positioning hole, so that the trapezoidal thread on the worm shaft (1) and the trapezoidal thread on the sleeve (15) remain disengaged, the adapter shaft (18) is subjected to the elastic force of the fourth spring (16), and the end face teeth mesh with the input shaft (17) of the aircraft generator; In the tripped state, the internal temperature of the aircraft generator exceeds the set threshold. The controller control coil (12) is energized, and magnetic force is generated through the iron core (11), causing the armature (10) to move against the elastic force of the third spring (13). The head disengages from the positioning hole, causing the worm shaft (1) to move under the elastic force of the second spring (4). The trapezoidal thread between the worm shaft (1) and the sliding sleeve (15) engages. The sliding sleeve (15) is driven to rotate by the adapter shaft (18) and the aircraft generator drive shaft (19) through the second connecting pin (20). Under the action of the trapezoidal thread, it slides along the axial direction of the aircraft generator drive shaft (19), causing the end face teeth between the adapter shaft (18) and the aircraft generator input shaft (17) to disengage. The iron core (11) is welded from three sections. The middle section is made of non-magnetic material. The mounting holes are formed on the front section, the middle section and the rear section. The third spring (13) is located between the rear section and the bottom of the armature (10). When the thermal trip mechanism of the aircraft generator is in the tripped state, the iron core (11) at the rear end is in conical contact with the bottom of the armature (10).

2. The thermal trip mechanism for an aircraft generator according to claim 1, characterized in that, Also includes: The pull rod (2) is set through the support hole, and has a first annular protrusion and a first guide groove on the side wall. One end has a first insertion hole; the first insertion hole is connected to the first guide groove; the worm shaft (1) is inserted into the first insertion hole, and the worm shaft (1) has a first pin hole. The first connecting pin (5) is provided in the first pin hole and the first guide groove; The first spring (6) is sleeved on the outer periphery of the pull rod (2), and its two ends are connected between the support seat (7) and the first annular protrusion.

3. The thermal tripping mechanism for an aircraft generator according to claim 2, characterized in that, The support hole has an anti-rotation notch; The pull rod (2) has anti-rotation grooves on its side wall; The thermal trip mechanism of the aircraft generator also includes: Anti-rotation pin (9) is set in anti-rotation notch and anti-rotation groove.

4. The thermal trip mechanism for an aircraft generator according to claim 3, characterized in that, The outer wall of the inner end of the adapter shaft (18) is splined with the side wall of the second insertion hole.

5. The thermal tripping mechanism for an aircraft generator according to claim 4, characterized in that, The support base (7) has a first positioning hole, and the first spring (6) is engaged in the first positioning hole; The support base (7) has a second positioning hole, and the second spring (4) is engaged in the second positioning hole; The bottom of the mounting hole has a third positioning hole, and the third spring (13) is locked in the third positioning hole; The inner end of the adapter shaft (18) has a fourth positioning hole, and the fourth spring (16) is locked in the fourth positioning hole.

6. The thermal trip mechanism for an aircraft generator according to claim 5, characterized in that, The output end of the aircraft generator input shaft (17) is mounted in the second insertion hole via a bearing.

7. The thermal trip mechanism for an aircraft generator according to claim 6, characterized in that, The pull rod (2) has a connecting through hole on the side wall of the end facing away from the worm shaft (1); The thermal trip mechanism for aircraft generators also includes: Pull ring (8) is locked in the connecting through hole.

8. The thermal trip mechanism for an aircraft generator according to claim 7, characterized in that, Also includes: Bushing (3) is fitted around the outer circumference of worm shaft (1) and has an annular pad on its outer wall; The annular pad is placed between the second spring (4) and the second annular protrusion.

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