A support structure within a high pressure turbine nozzle guide vane

Abstract

The application provides a high-pressure turbine guider inner support structure, comprising: an inner support ring assembly, the inner support ring assembly comprising an inner support ring and a pre-rotation rectification vane row, the pre-rotation rectification vane row and the inner support ring being integrally designed and manufactured by using Ti2AlNb light material; an inner sealing ring assembly, the inner sealing ring assembly comprising an inner sealing ring and a honeycomb ring installed on the inner sealing ring, wherein the base body of the inner sealing ring is made of high-temperature alloy material; and a clamping ring arranged between the inner support ring assembly and the inner sealing ring assembly and used for connecting the inner sealing ring assembly and the inner support ring assembly. Compared with a traditional integrally cast inner support structure, the high-pressure turbine guider inner support structure can be manufactured by machining, so that the manufacturing difficulty is low, the cost is low, the cycle is short, the manufacturing precision of the pre-rotation rectification vane row can be ensured, and the high-pressure turbine guider inner support structure has good application value.

Description

Technical Field

[0001] This application belongs to the field of aero-engine technology, and specifically relates to an internal support structure for a high-pressure turbine guide vane. Background Technology

[0002] The high-pressure turbine guide vane of an aero-engine is an important functional component for regulating the flow characteristics of the inlet gas of the high-pressure turbine. It also serves as an air intake channel for cooling the rotor blades of the high-pressure turbine.

[0003] like Figure 1 The diagram shows a schematic of the internal support structure of a high-pressure turbine guide vane in the prior art. The internal support structure 10 of the high-pressure turbine guide vane mainly includes an inner support ring 11, a duct 12, and a pre-swirl rectifier vane 13. The inner support ring 11 is arranged approximately parallel to the outer wall 16 of the main combustion chamber flame tube, forming a channel Q1 between them for supplying air to the high-pressure turbine guide vanes 15. A through hole is provided on the inner support ring 11 to form a channel Q2 for supplying air to the high-pressure turbine rotor blades (blades on the rear side of the high-pressure turbine guide vanes 15, not shown). The high-pressure turbine guide vane is usually connected and positioned to the casing 17 inside the main combustion chamber through the inner support ring 11, forming a maintenance unit together with the main combustion chamber.

[0004] To effectively organize airflow, a row of pre-rotating rectifier blades 13 is installed on the air supply channel of the high-pressure turbine rotor blades. To ensure interstage sealing between the high-pressure turbine guide vane and the rotor, an interstage duct structure 12 is also provided on the duct 12 when constructing the air supply channel of the rotor blades to ensure the smooth flow of the interstage sealing duct Q3.

[0005] The inner support ring 11 is the main component of the high-pressure turbine guide vane. All components of the air supply passages from the two air streams in the combustion chamber to the rotor blades must be connected to the inner support ring 11, together forming the inner support ring assembly. In existing technologies, the inner support ring is typically made of high-temperature alloy material. To control weight, the guide rings that construct the air supply passages for the rotor blades, the pre-swirl rectifier blades, and the ducts that construct the interstage bleed passages are usually directly welded to the inner support ring, rather than being connected by bolts.

[0006] For high-performance aero-engines, to effectively reduce weight, lightweight Ti2AlNb (a lightweight titanium alloy) material with good temperature resistance is sometimes used for the inner support ring. However, due to the poor weldability of Ti2AlNb, it is difficult to manufacture the inner support ring assembly using welding processes. To solve this problem, the inner support ring assembly is often manufactured using a one-piece casting process. However, the existing one-piece casting process for the inner support ring assembly made of lightweight Ti2AlNb material has two main drawbacks:

[0007] 1) The inner support ring assembly has a complex structure, and its manufacturing using casting technology is difficult, costly, and time-consuming.

[0008] 2) The shape and position dimensions of the pre-swirl rectifier blade grating are guaranteed by casting, but the dimensional accuracy is poor, making it difficult to guarantee the requirements of blade grating shape and channel area. Summary of the Invention

[0009] The purpose of this application is to provide an internal support structure for a high-pressure turbine guide to solve or mitigate at least one of the problems in the prior art.

[0010] The technical solution of this application is: an internal support structure for a high-pressure turbine guide vane, comprising:

[0011] An inner support ring assembly, comprising an inner support ring and a pre-swirl rectifier blade grid, wherein the pre-swirl rectifier blade grid and the inner support ring are manufactured using Ti2AlNb lightweight material through machining.

[0012] An inner sealing ring assembly, the inner sealing ring assembly including an inner sealing ring and a honeycomb ring mounted on the inner sealing ring, wherein the substrate of the inner sealing ring is made of a high-temperature alloy material;

[0013] A retaining ring is disposed between the inner support ring assembly and the inner sealing ring assembly to achieve the connection between the inner sealing ring assembly and the inner support ring assembly.

[0014] In a preferred embodiment of this application, the pre-swirl rectifier blades are implemented by milling and / or turning.

[0015] In a preferred embodiment of this application, the inner sealing ring and the honeycomb ring are welded together to form an integral structure.

[0016] In a preferred embodiment of this application, the substrate of the inner sealing ring is selected from a high-temperature alloy material with a linear expansion coefficient greater than that of Ti2AlNb in the inner support ring assembly, and the proportion of the greater coefficient is no more than 10%.

[0017] In a preferred embodiment of this application, the leading edge of the inner sealing ring is provided with a plurality of circumferentially distributed grooves, and the inner support ring is provided with a plurality of circumferentially distributed protrusions at the positions where it mates with the inner sealing ring. The circumferential positioning and anti-rotation of the inner sealing ring and the inner support ring are achieved through the cooperation of the grooves and protrusions.

[0018] In a preferred embodiment of this application, the outer surface of the inner sealing ring is provided with an outer semi-circular groove, and a through slot is provided at any position on the outer semi-circular groove. The inner support ring is provided with an inner semi-circular groove that is adapted to the outer semi-circular groove. The retaining ring is disposed in the circular groove formed by the outer semi-circular groove and the inner semi-circular groove, and the bent part of the retaining ring is inserted into the slot to achieve positioning.

[0019] In a preferred embodiment of this application, the leading edge of the pre-swirl rectifier blade is provided with a through hole, and the inner support ring and the inner sealing ring are respectively provided with a support ring through hole and a sealing ring through hole adapted to the through hole. The through hole, the support ring through hole and the sealing ring through hole together form an interstage air intake channel.

[0020] Compared with the traditional one-piece cast internal support structure, the internal support structure of this high-pressure turbine guide vane can be manufactured by machining, which is less difficult, less costly, and shorter in cycle, and can ensure the manufacturing accuracy of the pre-swirl rectifier blade cascade, thus having better application value. Attached Figure Description

[0021] To more clearly illustrate the technical solutions provided in this application, the accompanying drawings will be briefly described below. Obviously, the drawings described below are merely some embodiments of this application.

[0022] Figure 1 This is a schematic diagram of the internal support structure of a high-pressure turbine guide in the prior art.

[0023] Figure 2 This is a schematic diagram of the internal support structure of the high-pressure turbine guide in this application.

[0024] Figure 3 This is a schematic diagram of the inner support ring assembly structure of this application.

[0025] Figure 4 This is a schematic diagram of the internal sealing ring assembly structure of this application.

[0026] Figure 5 This is a schematic diagram showing the location of the groove in the inner sealing ring of this application.

[0027] Figure 6 This is a schematic diagram of the slot position in the inner sealing ring of this application.

[0028] Figure 7 This is a schematic diagram of the pre-rotating rectifier blade grid in the AA direction of the inner support ring assembly of this application.

[0029] Figure label:

[0030] 21-Inner Support Ring Assembly

[0031] 211-Inner Support Ring

[0032] 212-Pre-swirl rectifier cascade

[0033] 213-Through Hole

[0034] 214-protrusion

[0035] 215-Inner semi-circular groove

[0036] 22-Inner sealing ring assembly

[0037] 221-Inner Sealing Ring

[0038] 222-Cellular Ring

[0039] 223-Sealing ring through hole

[0040] 224-card slot

[0041] 225-groove

[0042] 23-Card Circle Detailed Implementation

[0043] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings.

[0044] like Figures 2 to 7 The high-pressure turbine guide inner support structure 20 provided in this application includes: an inner support ring assembly 21, an inner sealing ring assembly 22, and a retaining ring 23.

[0045] Combination Figure 3 As shown, the inner support ring assembly 21 includes an inner support ring 211 and a pre-swirl rectifier blade 212. The pre-swirl rectifier blade 212 and the inner support ring 211 are manufactured by machining and are made of Ti2AlNb lightweight material. The machining process is characterized by low cost, short cycle time, and the ability to ensure the manufacturing accuracy of the pre-swirl rectifier blade 212.

[0046] Combination Figure 4 As shown, the inner sealing ring assembly 22 includes an inner sealing ring 221 and a honeycomb ring 222 mounted on the inner sealing ring 221, wherein the substrate of the inner sealing ring 221 is made of a high-temperature alloy material. The inner sealing ring 221 and the honeycomb ring 222 can be welded into an integral structure. The high-temperature alloy material has good weldability, thereby enabling the welding of the substrate of the inner sealing ring 221 to the honeycomb ring 222.

[0047] In a preferred embodiment of this application, the substrate of the inner sealing ring 221 is made of a high-temperature alloy material with a linear expansion coefficient slightly greater than that of the inner support ring assembly Ti2AlNb. This ensures that when the inner sealing ring assembly 22 and the inner support ring assembly 21 are at similar operating temperatures, the radial free expansion of the inner sealing ring substrate is slightly greater than that of the inner support ring 211, thus ensuring that it is radially close to the pre-swirl rectifier blade 212 and together with the inner support ring assembly 21, forms a complete air intake channel.

[0048] Combination Figure 5As shown, the inner sealing ring 221 has multiple circumferentially distributed grooves 225 at its front edge, and multiple circumferentially distributed protrusions 214 at the position on the inner support ring 211 that mate with the inner sealing ring 221. Through the mate of the grooves 225 and the protrusions 214, the inner sealing ring 221 and the inner support ring 211 are circumferentially positioned and prevented from rotating.

[0049] Combination Figure 6 As shown, the inner sealing ring 221 has an outer semi-circular groove at the front, and a through slot 224 is provided at any position of the outer semi-circular groove. Correspondingly, the inner support ring 211 has an inner semi-circular groove 215 that matches the outer semi-circular groove. The retaining ring 23 is disposed between the outer semi-circular groove of the inner sealing ring 221 and the inner semi-circular groove 215 of the inner support ring 211, and the bent part of the retaining ring 23 is inserted into the slot 224 to achieve positioning.

[0050] Combination Figure 7 As shown, the leading edge of the pre-swirl rectifier blade 212 is provided with a through hole 213. The inner support ring 211 and the inner sealing ring 221 are respectively provided with support ring through holes and sealing ring through holes 223 adapted to the through holes 213. The three together form an interstage air intake channel.

[0051] The assembly process of the high-pressure turbine guide vane inner support structure of this application is as follows: First, the inner support ring assembly 21 is installed and fixed to the lower end of the combustion chamber casing and turbine rotor blades. Then, the inner sealing ring assembly 22 is axially pushed into the right end of the inner support ring assembly 21. The inner support ring assembly 21 and the inner sealing ring assembly 22 are circumferentially positioned and anti-rotation is achieved by the protrusion 214 and the groove 225. Finally, the retaining ring 23 is installed. The retaining ring 23 is inserted into the circular groove between the two rings along the retaining groove 224 for a suitable length, and one end of the retaining ring 23 is bent to prevent it from coming out during operation.

[0052] Compared with the traditional integrated casting internal support structure, the high-pressure turbine guide vane internal support structure of this application can be manufactured by machining, which is less difficult to manufacture, less costly, and shorter in cycle, and can ensure the manufacturing accuracy of the pre-swirl rectifier blade cascade, thus having good application value.

[0053] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A support structure within a high pressure turbine nozzle characterized by, include: The inner support ring assembly (21) includes an inner support ring (211) and a pre-swirl rectifier blade grating (212), wherein the pre-swirl rectifier blade grating (212) and the inner support ring (211) are manufactured by machining Ti2AlNb material; An inner sealing ring assembly (22) includes an inner sealing ring (221) and a honeycomb ring (222) mounted on the inner sealing ring (221), wherein the substrate of the inner sealing ring (221) is made of a high-temperature alloy material; A retaining ring (23) is disposed between the inner support ring assembly (21) and the inner sealing ring assembly (22) to realize the connection between the inner sealing ring assembly (22) and the inner support ring assembly (21).

2. The high pressure turbine nozzle inner support structure as in claim 1, wherein, The pre-rotating rectifier blade (212) is achieved by milling and / or turning.

3. The high pressure turbine nozzle inner support structure as in claim 1, wherein, The inner sealing ring (221) and the honeycomb ring (222) are welded together to form an integral structure.

4. The high pressure turbine nozzle inner support structure as in claim 1, wherein, The substrate of the inner sealing ring (221) is made of a high-temperature alloy material with a linear expansion coefficient greater than that of the inner support ring assembly, and the proportion of the coefficient greater does not exceed 10%.

5. The high pressure turbine guide vane inner support structure as in claim 1, wherein, The inner sealing ring (221) has multiple circumferentially distributed grooves (225) at its front edge, and the inner support ring (211) has multiple circumferentially distributed protrusions (214) at the position where it mates with the inner sealing ring (221). The circumferential positioning and anti-rotation of the inner sealing ring (221) and the inner support ring (211) are achieved through the cooperation of the grooves (225) and the protrusions (214).

6. The high pressure turbine guide inner support structure as in claim 5, wherein, The outer surface of the inner sealing ring (221) is provided with an outer semi-circular groove, and a through slot (224) is provided at any position on the outer semi-circular groove. The inner support ring (211) is provided with an inner semi-circular groove (215) that is adapted to the outer semi-circular groove. The retaining ring (23) is set in the circular groove formed by the outer semi-circular groove and the inner semi-circular groove (215), and the bent part of the retaining ring (23) is inserted into the slot (224) to achieve positioning.

7. The high pressure turbine guide vane inner support structure as in claim 6, wherein, The leading edge of the pre-rotating rectifier blade (212) is provided with a through hole (213). The inner support ring (211) and the inner sealing ring (221) are respectively provided with a support ring through hole and a sealing ring through hole (223) adapted to the through hole (213). The through hole (213), together with the support ring through hole and the sealing ring through hole (223), form a channel for interstage air intake.

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