Rear baffle structure of gas turbine disc

Abstract

The invention belongs to the technical field of aero-engines, and provides a gas turbine disc rear baffle structure which comprises a baffle, a turbine disc and a check ring, a limiting groove is formed in the turbine disc, the check ring is arranged in the limiting groove, one part of the baffle is matched with the limiting groove and the check ring, and the other part of the baffle abuts against the turbine disc. The baffle comprises a fixing part, a supporting part and a pressing part which are connected in sequence, the fixing part is arranged in the limiting groove, the part structure, close to the check ring, of the fixing part is connected with the check ring in a clamped mode, the part structure, close to an outlet of the limiting groove, of the fixing part is in transition fit or interference fit with the limiting groove, the pressing part abuts against the turbine disc, and a protruding part is arranged at the end of the pressing part. The thickness of the joint of the pressing part and the supporting part is the same, and the ratio of the thickness of the supporting part to the structural thickness of the part, away from the supporting part, of the pressing part is at least 2. Heat of the supporting part is prevented from being transmitted to the pressing part, the temperature reduction speed of the supporting part is reduced, the temperature difference between the supporting part and the turbine disc is reduced, the fixing part is prevented from being disengaged from the limiting groove, and circumferential rotation prevention is achieved.

Description

Technical Field

[0001] The present invention belongs to the technical field of aeroengines, and particularly relates to a rear baffle structure for a gas turbine disk. Background Art

[0002] At present, most engines use front and rear baffles to axially limit the working blades of a gas turbine disk. Specifically, the gas turbine disk and the rear baffle are connected by bolts for circumferential positioning, or are connected to the gas turbine disk in the form of a boltless baffle. The circumferential anti-rotation is generally achieved by the cooperation and positioning of the boss on the working blade and the groove on the baffle. Using the bolt connection method will increase the number of parts and the assembly difficulty. At the same time, the existence of bolt holes leads to stress concentration, reducing the life of the baffle. While using the boltless baffle with boss and groove structures will also increase the stress concentration area and make the processing difficulty larger, increasing the manufacturing cost. Summary of the Invention

[0003] In view of the above problems, the present invention provides a rear baffle structure for a gas turbine disk, including: a baffle, a turbine disk, and a retaining ring. A limiting groove is provided on the turbine disk, the retaining ring is arranged in the limiting groove, a part of the baffle cooperates with the limiting groove and the retaining ring respectively, and the other part abuts against the turbine disk. The baffle includes a fixed part, a supporting part, and a pressing part connected in sequence. The fixed part is arranged in the limiting groove, and the structure of the part of the fixed part close to the retaining ring is clamped with the retaining ring. The structure of the part of the fixed part close to the outlet of the limiting groove is in transitional fit or interference fit with the limiting groove, and the pressing part abuts against the turbine disk. A protruding part is provided at the end of the pressing part. The thickness at the connection of the pressing part and the supporting part is the same. The ratio of the thickness of the supporting part to the thickness of the structure of the part of the pressing part away from the supporting part is at least 2.

[0004] Optionally, the thickness of the pressing part is between 3.5 - 6 mm.

[0005] Optionally, the pressing part inclines towards the turbine disk direction to form a preset inclination angle.

[0006] Optionally, the inclination angle is between 15° ≤ θ ≤ 40°.

[0007] Optionally, a pressing end face is provided at the end of the pressing part, and the pressing end face is connected to the protruding part.

[0008] Optionally, the pressing end face is in an arched structure.

[0009] Optionally, the distance between the pressing end face close to the turbine disk and the inner wall of the retaining ring is H1.

[0010] Optionally, an installation hook is provided at the outlet of the limit groove, and the distance between the inner wall of the installation hook and the outer wall of the turbine disk is H2.

[0011] Optionally, the retaining ring has an L-shaped structure, and the axial thickness of the retaining ring is H3.

[0012] Optionally, a sealing groove is provided on the pressing portion, and a sealing wire is provided in the sealing groove.

[0013] The present invention has the following advantages compared with the prior art:

[0014] Through the turbine disk and the baffle, without increasing the bolt hole structure and without providing the boss and groove structures, by setting the corresponding protruding portions, a lever effect towards the pressing portion is formed under the centrifugal load in the working state, ensuring that the pressing portion firmly fits the end face of the turbine disk, with reliable work. Moreover, the thickness at the connection between the pressing portion and the supporting portion is the same, and the thickness of the part of the pressing portion away from the supporting portion is more than twice thinner than the thickness of the supporting portion. During the emergency stop process, it can effectively inhibit the heat of the supporting portion from being transferred to the pressing end face portion, reduce the speed of temperature reduction of the supporting portion, reduce the temperature difference from the turbine disk, prevent the fixing portion from disengaging from the limit groove, ensure the circumferential anti-rotation effect, and the cooperation between the fixing portion, the limit groove and the retaining ring can achieve the axial limit of the blade, ensuring the long-term working life requirements of the turbine disk, and reducing the processing difficulty and cost.

[0015] Other features and advantages of the present invention will be described in the following specification, and, in part, will become obvious from the specification, or will be understood by implementing the present invention. The objectives and other advantages of the present invention can be achieved and obtained through the structures pointed out in the specification and the drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] In order to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings required for the description of the embodiments or the prior art. Obviously, the following drawings are some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other drawings can be obtained based on these drawings.

[0017] Figure 1 Shows the schematic diagram of the rear baffle structure of the gas turbine disk in the embodiment of the present invention;

[0018] Figure 2 Shows the inclination schematic diagram of the pressing portion of the rear baffle structure of the gas turbine disk in the embodiment of the present invention;

[0019] Figure 3 Shows the schematic diagram of the position of the pressing end face of the rear baffle structure of the gas turbine disk in the embodiment of the present invention;

[0020] Figure 4 Shows a schematic diagram of the installation hook position of the rear baffle structure of the gas turbine disk in the embodiment of the present invention;

[0021] Figure 5 Shows a schematic diagram of the retaining ring of the rear baffle structure of the gas turbine disk in the embodiment of the present invention.

[0022] In the figure, 1 is the baffle; 10 is the sealing groove; 11 is the fixing part; 12 is the supporting part; 13 is the pressing part; 14 is the protruding part; 15 is the pressing end face; 2 is the turbine disk; 3 is the retaining ring; 4 is the sealing wire; 5 is the installation hook; 21 is the limiting groove. Specific embodiments

[0023] In order to make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are some, but not all, of the embodiments of the present invention. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts shall fall within the protection scope of the present invention.

[0024] As Figure 1 shown, the present invention provides a rear baffle structure of a gas turbine disk, including: a baffle 1, a turbine disk 2, and a retaining ring 3. A limiting groove 21 is provided on the turbine disk 2, the retaining ring 3 is arranged in the limiting groove 21, a part of the baffle 1 is respectively matched with the limiting groove 21 and the retaining ring 3, and the other part abuts against the turbine disk 2. The baffle 1 includes a fixing part 11, a supporting part 12, and a pressing part 13 connected in sequence. The fixing part 11 is arranged in the limiting groove 21, and the structure of the part of the fixing part 11 close to the retaining ring 3 is clamped with the retaining ring 3. The structure of the part of the fixing part 11 close to the outlet of the limiting groove 21 is in transitional fit or interference fit (this interference fit can be a small interference fit) with the limiting groove 21, and the pressing part 13 abuts against the turbine disk 2. A protruding part 14 is provided at the end of the pressing part 13. The thickness at the connection between the pressing part 13 and the supporting part 12 is the same. The ratio of the thickness of the supporting part 12 to the thickness of the structure of the part of the pressing part 13 far from the supporting part 12 is at least 2, that is, the thickness of the structure of the part of the pressing part 13 far from the supporting part 12 is more than twice thinner than the thickness of the supporting part 12. Through the protruding part 14, a lever effect towards the pressing part 13 is formed under the centrifugal load in the working state, ensuring that the pressing surface is firmly attached and the work is reliable. For the different thickness settings between the supporting part 12 and the pressing part 13, during the emergency stop process, the heat of the supporting part 12 can be effectively inhibited from being transmitted to the pressing end face 15 part, reducing the speed of temperature reduction of the supporting part 12, reducing the temperature difference from the turbine disk 2, preventing the fixing part 11 from disengaging, and ensuring the circumferential anti-rotation effect. Moreover, the mutual cooperation between the fixing part 11, the supporting part 12, and the limiting groove 21 also realizes the axial limitation of the turbine disk 2.

[0025] In one embodiment, the thickness of the pressing portion 13 is between 3.5 and 6 millimeters. Optionally, the thickness of the pressing portion 13 is 4, 5, or 6 millimeters, and the thickness of the portion of the pressing portion 13 away from the supporting portion 12 is at least less than 2, 2.5, or 3. In addition to taking these thicknesses, the pressing portion 13 can also be valued within the range of 3.5 - 6 millimeters as needed.

[0026] As Figure 2 shown, in one embodiment, the pressing portion 13 is inclined towards the turbine disk 2 to form a preset inclination angle. Through this setting method, one end of the pressing portion 13 has a thicker thickness and the other end has a thinner thickness, and the thickness difference between the two is more than twice. During initial assembly, a force is applied to the supporting portion 12 to cause pre - deformation of the pressing portion 13 towards the turbine disk 2, storing initial strain energy. During the parking process, when the baffle 1 is affected by centrifugal force and the pressing end face 15 of the pressing portion 13 disengages from the turbine disk 2, it is necessary to overcome the initial strain energy of the pressing portion 13. Therefore, it can play a role in inhibiting the disengagement of the pressing end face 15 of the baffle 1 from the end face of the turbine disk 2. On the other hand, the pressing portion 13 is inclined towards the turbine disk 2, which can also form a support for pressing towards the turbine disk 2 to prevent the pressing end face 15 from disengaging. In addition, the supporting portion 12 is thicker than the fixing portion 11 and the pressing portion 13 in the baffle 1, and the supporting portion 12 has the thickest thickness.

[0027] In one embodiment, the inclination angle is between 15°≤θ≤40°. Optionally, the inclination angle can be 18°, 20°, 22°, 25°, 28°, 30°, 33°, 35°, 40°. Specifically, the inclination angle can be 20°≤θ≤30°. For example, it can be optionally 20°, 23°, 26°, 30°, etc.

[0028] In one embodiment, a pressing end face 15 is provided at the end of the pressing portion 13, and the pressing end face 15 is connected to the protruding portion 14. Through the protruding portion 14, a lever effect towards the pressing end face 15 is formed under centrifugal load during the working state, ensuring that the pressing end face 15 firmly adheres to the end face of the turbine disk 2 and the work is reliable. It should be noted that the protruding portion 14 directly acts on the pressing end face 15, and the pressing end face 15 is in an arched structure. Through the arched structure, the structural strength of the pressing end face 15 is increased, avoiding structural damage to the pressing end face 15 due to excessive pressure.

[0029] As Figure 3As shown, in one embodiment, the distance between the pressing end face 15 close to the turbine disk 2 and the inner wall of the retaining ring 3 is H1. By setting H1, the fixing parts 11 in the baffle 1 cooperate with the limiting groove 21 and the retaining ring 3 respectively, ensuring that the pressing end face 15 generates pre-deformation to tightly fit with the end face of the turbine disk 2. The protruding part 14 forms a lever effect under the action of the centrifugal load to ensure that the pressing end face 15 is tightly pressed and does not come off.

[0030] As Figure 4 shown, in one embodiment, an installation hook 5 is provided at the outlet of the limiting groove 21. The distance between the inner wall of the installation hook 5 and the outer wall of the turbine disk 2 is H2. The installation hook 5 can block part of the limiting groove 21, preventing the retaining ring 3 from falling out of the limiting groove 21. By setting the distance H2, it is ensured that the fixing parts 11 cooperate accurately with the limiting groove 21 and the retaining ring 3 respectively, and further ensure that the pressing end face 15 generates pre-deformation to tightly fit with the end face of the turbine disk 2.

[0031] As Figure 5 shown, in one embodiment, the retaining ring 3 has an L-shaped structure, and the axial thickness of the retaining ring 3 is H3. By setting H3, it is ensured that the fixing parts 11 are precisely matched with the limiting groove 21, thereby ensuring that the pressing end face 15 can tightly fit with the end face of the turbine disk 2. It should be noted that through the above H1, H2, and H3, the fixing parts 11 are precisely matched with the limiting groove 21 and the retaining ring 3 respectively, and it is also ensured that the pressing end face 15 can tightly fit with the end face of the turbine disk 2. Finally, the pressing end face 15 is pressed by the action of the protruding part 14, so that the pressing end face 15 presses the end face of the turbine disk 2. In addition, a limiting structure can be formed between the L-shaped retaining ring 3 and the limiting groove 21. A part of the fixing part 11 is arranged in the limiting structure. The inner wall of the limiting groove 21 on the opposite side of the limiting structure and the outer wall of the fixing part 11 adopt a transition fit or an interference fit. Specifically, the outer wall of the fixing part 11 is a cylindrical surface, which is convenient for cooperating with the inner wall of the limiting groove 21.

[0032] In one embodiment, a sealing groove 10 is provided on the pressing part 13, and a sealing wire 4 is arranged in the sealing groove 10. Specifically, the sealing groove 10 is used for assembling the sealing wire 4 to seal the cold air of the cooling gas turbine working blade.

[0033] In summary, when the engine starts, the baffle 1 of the turbine disk 2 is subjected to centrifugal force, and the protruding portion 14 can act on the pressing end face 15, so that the pressing end face 15 firmly fits on the end face of the turbine disk 2. The circumferential anti-rotation function of the baffle 1 of the gas turbine disk 2 is realized through the frictional force generated by pressing. During the engine shutdown process, on the one hand, during the initial assembly process of the pressing portion 13, due to the applied pressing force, pre-deformation occurs and initial strain energy is stored, which can prevent the baffle 1 of the high-pressure turbine disk 2 from being separated from the end face of the turbine disk 2 due to centrifugal force during the engine operation, so that the pressing end face 15 can firmly fit on the end face of the turbine disk 2, and the circumferential anti-rotation of the baffle 1 of the gas turbine disk 2 is realized through the frictional force generated by pressing. On the other hand, since the baffle 1 of the gas turbine disk 2 dissipates heat faster than the turbine disk 2, the supporting portion 12 is provided with a thicker wall thickness, which can increase the heat capacity of the baffle 1 of the turbine disk 2. At the same time, a part of the pressing portion 13 has a small thickness, which can reduce the speed of heat transfer from the supporting portion 12 to the pressing end face 15, thereby slowing down the cooling speed of the supporting portion 12, reducing the temperature difference from the turbine disk 2, preventing the fixing portion 11 from disengaging from the limiting groove 21, and ensuring the circumferential anti-rotation effect.

[0034] In this technical solution, the baffle 1 of the turbine disk 2 realizes the axial limitation of the blade and the circumferential limitation function of the rear baffle 1 of the gas turbine disk 2 relative to the turbine disk 2 without adding bolt hole structures and without setting boss and groove structures, ensuring the long-term working life requirements of the turbine rotor.

[0035] Although the present invention has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that: they can still modify the technical solutions described in the foregoing embodiments, or perform equivalent replacements for some of the technical features; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A rear baffle structure for a gas turbine disk, characterized in that, Including: A baffle plate (1), a turbine disk (2) and a retaining ring (3). A limiting groove (21) is provided on the turbine disk (2). The retaining ring (3) is arranged in the limiting groove (21). A part of the baffle plate (1) cooperates with the limiting groove (21) and the retaining ring (3) respectively, and the other part abuts against the turbine disk (2). The baffle plate (1) includes a fixed part (11), a supporting part (12) and a pressing part (13) connected in sequence. The fixed part (11) is arranged in the limiting groove (21), and a part of the structure of the fixed part (11) close to the retaining ring (3) is clamped with the retaining ring (3). A part of the structure of the fixed part (11) close to the outlet of the limiting groove (21) is in transitional fit or interference fit with the limiting groove (21). And the pressing part (13) abuts against the turbine disk (2). A protruding part (14) is provided at the end of the pressing part (13). The thickness at the connection of the pressing part (13) and the supporting part (12) is the same. The ratio of the thickness of the supporting part (12) to the thickness of the part of the structure of the pressing part (13) far from the supporting part (12) is at least 2.

2. The gas turbine disk rear baffle structure according to claim 1, characterized in that, The thickness of the pressing part (13) is between 3.5 and 6 millimeters.

3. The gas turbine disk rear baffle structure according to claim 1, characterized in that The pressing part (13) inclines towards the turbine disk (2) direction and forms a preset inclination angle.

4. The gas turbine disk rear baffle structure according to claim 3, characterized in that, The inclination angle is between 15° ≤ θ ≤ 40°.

5. The gas turbine disk rear baffle structure according to claim 1, wherein, A pressing end face (15) is provided at the end of the pressing part (13), and the pressing end face (15) is connected with the protruding part (14).

6. The gas turbine disk rear baffle structure according to claim 5, characterized in that, The pressing end face (15) is in an arched structure.

7. The gas turbine disk rear baffle structure according to claim 5, characterized in that, The distance between the pressing end face (15) close to the turbine disk (2) and the inner wall of the retaining ring (3) is H1.

8. The gas turbine disk rear baffle structure according to claim 1, wherein An installation hook (5) is provided at the outlet of the limiting groove (21). The distance between the inner wall of the installation hook (5) and the outer wall of the turbine disk (2) is H2.

9. The gas turbine disk rear baffle structure according to claim 1, characterized in that, The retaining ring (3) is in an L-shaped structure, and the axial thickness of the retaining ring (3) is H3.

10. The gas turbine disk rear baffle structure according to claim 1, characterized in that, A sealing groove (10) is provided on the pressing part (13), and a sealing wire (4) is arranged in the sealing groove (10).

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