Aircraft turbine protective cover

Abstract

The utility model discloses an aircraft turbine protective cover which comprises a cover body, a conical surface protective net is installed on one side in the cover body, and a supporting buffer assembly is installed on the side, located on the conical surface protective net, in the cover body. The supporting and buffering assembly comprises a supporting column installed in the middle of the interior of the conical surface protection net, four connecting rods annularly installed on the outer wall of the supporting column, sliding sleeves installed at the ends, away from the supporting column, of the connecting rods, and fixing rods penetrating through the sliding sleeves. The fixing ring is arranged between the fixing rods; and the spring is arranged between the fixing ring and the sliding sleeve. The protective cover has the beneficial effects that the conical surface protective net is arranged on the cover body at the front end of the aircraft turbine, and the supporting and buffering assembly is used for supporting and buffering along with the conical surface protective net, so that the protective cover can effectively prevent flying objects such as flying birds from directly colliding with turbine fan blades when being used; and the damage to the fan blades of the turbine wheel of the aircraft when an accidental collision accident occurs is prevented.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft turbine protection, in particular to an aircraft turbine protection cover. Background Art

[0002] Aircraft turbine shrouds generally refer to the turbine engine covers or shields installed on the front of aircraft engines. These shields are used to protect the engine from the external environment and debris, while also helping to optimize engine performance and airflow dynamics.

[0003] At present, the aircraft turbine shield is mainly composed of a cylindrical shell and an annular cover installed at the front end of the shell. Although the aircraft turbine shield of this structure can provide certain protection for the aircraft turbine when in use, the annular cover at the front end of the shield is a straight-through structure, so that the fan blades of the aircraft turbine are in direct contact with the external environment when working. It is easy for flying objects such as birds to accidentally enter the flight altitude of the wind turbine, causing the flying objects to directly collide with the aircraft turbine blades, thereby causing damage to the aircraft turbine blades, resulting in poor protection performance of the aircraft turbine shield. Utility Model Content

[0004] 1. Technical issues to be resolved

[0005] The technical problem to be solved by the utility model is to provide an aircraft turbine protective cover which can shield and protect the fan turbine blades of the fan without excessively affecting the aircraft turbine air intake in view of the current status of the prior art.

[0006] (II) Technical solution

[0007] The utility model is achieved through the following technical scheme: the utility model proposes an aircraft turbine shield, including a shield body, a conical protective net is installed on one side of the shield body, a support buffer assembly is installed on the shield body at one side of the conical protective net, the support buffer assembly includes a support column installed in the middle of the conical protective net, four connecting rods installed in a ring shape on the outer wall of the support column, a sliding sleeve installed at one end of the connecting rod away from the support column, a fixing rod passing through the sliding sleeve, a fixing ring installed between the fixing rods, and a spring installed between the fixing ring and the sliding sleeve.

[0008] Furthermore, the frame of the conical surface protective net is connected to the cover body by bolts, and the conical surface protective net is a stainless steel protective net.

[0009] By adopting the above technical solution, the conical protective net has a porous structure, which can protect the air entering the aircraft turbine blades while avoiding excessive impact on the air intake of the aircraft turbine blades.

[0010] Furthermore, the support column is welded to the conical protective net, one end of the connecting rod is hinged to the support column, and the other end of the connecting rod is hinged to the sliding sleeve.

[0011] By adopting the above technical solution, it is possible to ensure that the connecting rod can rotate conveniently relative to the sliding sleeve and the supporting column.

[0012] Furthermore, one end of the fixing rod is welded to the cover body, and the other end of the fixing rod is welded to the fixing ring.

[0013] By adopting the above technical solution, the fixing rod is mainly used to achieve reliable fixation of the fixing ring.

[0014] Furthermore, the sliding sleeve is slidably connected to the fixing rod, the fixing rod passes through the spring, one end of the spring is welded to the sliding sleeve, and the other end of the spring is welded to the fixing ring.

[0015] By adopting the above technical solution, the fixing ring has a hollow structure, which can ensure the normal flow of air to the aircraft turbine blades. When the conical protective net is deformed by the impact of a flying object, the support column will apply pressure to the sliding sleeve through the connecting rod to make the sliding sleeve slide along the fixing rod, and the spring is in a pulled state. When the impact is completed, the spring will drive the sleeve to reset, thereby assisting the recovery of the elastic deformation of the conical protective net with the help of the connecting rod and the support rod.

[0016] Furthermore, a connecting screw groove connected to a screw boss pre-set on the aircraft turbine housing is provided on one side wall of the cover body, and the connecting screw groove is an annular structure.

[0017] By adopting the above technical solution, the reliable installation of the front end of the aircraft turbine housing of the cover can be ensured under the action of the connecting screw groove.

[0018] Furthermore, a second internal thread is formed on one side wall of the connecting screw groove, and a first internal thread is formed on the other side wall of the connecting screw groove.

[0019] By adopting the above technical solution, the first internal thread and the second internal thread enable the cover body to have a double locking function after being fixed, and the installation is more secure.

[0020] (III) Beneficial effects

[0021] Compared with the prior art, the utility model has the following beneficial effects:

[0022] In order to solve the problem that the current aircraft turbine shield is mainly composed of a cylindrical shell and an annular cover installed at the front end of the shell, although the aircraft turbine shield of this structure can provide certain protection for the aircraft turbine when in use, the annular cover at the front end of the shield is a straight-through structure, so that the fan blades of the aircraft turbine are in direct contact with the external environment when working, and it is easy for flying objects such as birds to accidentally enter the flight altitude of the fan, causing the flying objects to directly collide with the aircraft turbine blades, thereby causing damage to the aircraft turbine blades, resulting in poor protection performance of the aircraft turbine shield. The utility model installs a conical protective net on the cover body at the front end of the aircraft turbine, and uses a supporting buffer component to support and buffer the conical protective net, so that the protective cover can effectively avoid direct collision between flying objects such as birds and the turbine blades when in use, prevent damage to the aircraft turbine wheel blades in the event of an accidental collision, and improve the overall protection performance of the turbine shield. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 It is a structural schematic diagram of an aircraft turbine protective cover described in the utility model;

[0024] Figure 2 It is a main cross-sectional view of an aircraft turbine protective cover described in the utility model;

[0025] Figure 3 It is a right side view of a fixing ring and a fixing rod in an aircraft turbine protective cover described in the utility model.

[0026] The following are the descriptions of the reference numerals:

[0027] 1. Cover body; 2. Conical protective net; 3. Connecting screw groove; 4. Internal thread 2; 5. Support buffer assembly; 501. Fixed rod; 502. Support column; 503. Connecting rod; 504. Sliding sleeve; 505. Spring; 506. Fixed ring; 6. Internal thread 1. DETAILED DESCRIPTION

[0028] In order to make the purpose, technical solution and advantages of the utility model more clear, the utility model is further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described here are only used to explain the utility model and are not used to limit the utility model.

[0029] like Figure 1-Figure 3As shown, an aircraft turbine shield in this embodiment includes a shield body 1, a conical protective net 2 is installed on one side of the shield body 1, and the conical protective net 2 is a porous structure. While protecting the aircraft turbine blades, it can avoid excessive impact on the air intake of the aircraft turbine blades. A support buffer assembly 5 is installed on one side of the conical protective net 2 in the shield body 1. The support buffer assembly 5 includes a support column 502 installed in the middle of the conical protective net 2, four connecting rods 503 installed in an annular shape on the outer wall of the support column 502, a sliding sleeve 504 installed at one end of the connecting rod 503 away from the support column 502, and a fixing rod 501 penetrating the sliding sleeve 504. , a fixing ring 506 installed between the fixing rods 501 and a spring 505 installed between the fixing ring 506 and the sliding sleeve 504. The fixing ring 506 is a hollow structure, which can ensure the normal flow of air to the aircraft turbine blades. When the conical protective net 2 is deformed by the impact of a flying object, the support column 502 will apply pressure to the sliding sleeve 504 through the connecting rod 503 to make the sliding sleeve 504 slide along the fixing rod 501, and the spring 505 is in a pulled state. When the impact is completed, the spring 505 will drive the sleeve to reset, thereby assisting the recovery of the elastic deformation of the conical protective net 2 with the help of the connecting rod 503 and the support rod.

[0030] like Figure 1-Figure 3 As shown, in this embodiment, the frame of the conical protective net 2 is bolted to the cover body 1, the conical protective net 2 is a stainless steel protective net, the support column 502 is welded to the conical protective net 2, one end of the connecting rod 503 is hinged to the support column 502, and the other end of the connecting rod 503 is hinged to the sliding sleeve 504, which can ensure the convenient rotation of the connecting rod 503 relative to the sliding sleeve 504 and the support column 502, one end of the fixing rod 501 is welded to the cover body 1, and the other end of the fixing rod 501 is welded to the fixing ring 506, the fixing rod 501 is mainly used to achieve reliable fixation of the fixing ring 506, the sliding sleeve 504 is slidably connected to the fixing rod 501, the fixing rod 501 passes through the spring 505, and one end of the spring 505 is welded to the sliding sleeve 504, and the other end of the spring 505 is welded to the fixing ring 506.

[0031] like Figure 2 As shown, in this embodiment, a connecting screw groove 3 connected to a screw boss pre-set on the aircraft turbine housing is provided on one side wall of the cover body 1. The connecting screw groove 3 is an annular structure. Under the action of the connecting screw groove 3, the front end of the aircraft turbine housing of the cover body 1 can be reliably installed. An internal thread 2 4 is formed on one side wall of the connecting screw groove 3, and an internal thread 1 6 is formed on the other side wall of the connecting screw groove 3. The internal thread 1 6 and the internal thread 2 4 enable the cover body 1 to have a dual locking function after being fixed, and the installation is more secure.

[0032] The specific implementation process of this embodiment is as follows: when in use, the cover body 1 is first reliably installed on the screw platform pre-installed at the front end of the aircraft turbine housing with the help of the connecting screw groove 3, and then the protective cover can be put into use. During use, when a flying object hits the aircraft turbine blade, the flying object can be blocked by the conical protective net 2. When the conical protective net 2 is deformed by the impact of the flying object, the support column 502 will apply pressure to the sliding sleeve 504 through the connecting rod 503 to make the sliding sleeve 504 slide along the fixed rod 501, and the spring 505 is in a pulled state. When the impact is completed, the spring 505 will drive the sleeve to reset, thereby assisting the recovery of the elastic deformation of the conical protective net 2 with the help of the connecting rod 503 and the support column 502.

[0033] The above description of the disclosed embodiments enables those skilled in the art to implement or use the present invention. Various modifications to these embodiments will be apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the present invention. Therefore, the present invention will not be limited to the embodiments shown herein, but will conform to the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. An aircraft turbine shield, characterized in that: The invention comprises a cover body (1), a conical protective net (2) being installed on one side of the cover body (1), a support buffer assembly (5) being installed on one side of the conical protective net (2) in the cover body (1), the support buffer assembly (5) comprising a support column (502) installed in the middle of the conical protective net (2), four connecting rods (503) installed in an annular shape on the outer wall of the support column (502), a sliding sleeve (504) installed at one end of the connecting rod (503) away from the support column (502), a fixing rod (501) passing through the sliding sleeve (504), a fixing ring (506) installed between the fixing rods (501), and a spring (505) installed between the fixing ring (506) and the sliding sleeve (504).

2. The aircraft turbine shield according to claim 1, characterized in that: The frame of the conical surface protective net (2) is connected to the cover body (1) by bolts, and the conical surface protective net (2) is a stainless steel protective net.

3. The aircraft turbine shield according to claim 1, characterized in that: The support column (502) is welded to the conical protective net (2), one end of the connecting rod (503) is hinged to the support column (502), and the other end of the connecting rod (503) is hinged to the sliding sleeve (504).

4. The aircraft turbine shield according to claim 1, characterized in that: One end of the fixing rod (501) is welded to the cover body (1), and the other end of the fixing rod (501) is welded to the fixing ring (506).

5. The aircraft turbine shield according to claim 1, characterized in that: The sliding sleeve (504) is slidably connected to the fixing rod (501), the fixing rod (501) passes through the spring (505), one end of the spring (505) is welded to the sliding sleeve (504), and the other end of the spring (505) is welded to the fixing ring (506).

6. The aircraft turbine shield according to claim 1, characterized in that: A connecting screw groove (3) connected to a screw boss pre-set on an aircraft turbine housing is provided on one side wall of the cover body (1); the connecting screw groove (3) is an annular structure.

7. The aircraft turbine shield according to claim 6, characterized in that: A second internal thread (4) is formed on one side wall of the connecting screw groove (3), and a first internal thread (6) is formed on the other side wall of the connecting screw groove (3).

Images