A rotor axial force adjustment structure for a dual-rotor turbine performance test specimen

Abstract

This application provides a rotor axial force adjustment structure for a dual-rotor turbine performance test piece, comprising: a high-pressure turbine rotor disc assembly; a high-pressure turbine shaft connected to the high-pressure turbine rotor disc assembly; a high-pressure gear coupling connected to the high-pressure turbine shaft, wherein a balance disc is connected to the high-pressure gear coupling; an intake bearing housing, wherein a second sealing ring and a first sealing ring connected to the second sealing ring are fixed on the intake bearing housing, and the first sealing ring, the second sealing ring, the balance disc, and the high-pressure gear coupling form a balance cavity with the high-pressure turbine shaft; wherein, an induction pipe is connected to the first sealing ring, and balancing air is introduced from the induction pipe to form a balancing force acting on the balance disc in the balance cavity, thereby adjusting the axial force of the high-pressure turbine rotor.

Description

Technical Field

[0001] This application belongs to the field of aero-engine testing, and specifically relates to a rotor axial force adjustment structure for a dual-rotor turbine performance test piece. Background Technology

[0002] Axial force balance of the turbine rotor is a crucial issue that must be addressed in the design of turbine performance test specimens. Due to aerodynamic forces and disk pressure, the turbine rotor inevitably experiences axial forces, which are borne by ball bearings. Excessive axial forces can prevent the test specimen from functioning properly and may even compromise test safety. The design requirement for axial force balance in turbine performance test specimens is to ensure that the axial forces carried during operation remain within a reasonable range, and that reversal is not permitted during testing.

[0003] like Figure 1 The diagram shows the axial force balance structure of a single rotor turbine test piece. For the single rotor turbine performance test, the turbine rotor 11 is subjected to the main channel aerodynamic force F1 and the turbine disk front chamber pressure F2, both of which are in the rear direction (same as the main airflow direction). In order to ensure that the axial force of the turbine rotor is within a reasonable range, a balancing gas 12 can be introduced into the rear balancing chamber to provide a balancing force F3, ensuring that the axial force meets the bearing usage requirements.

[0004] To improve the design capabilities for matching high- and low-pressure turbines, the need for designing and testing dual-rotor turbine performance test specimens is becoming increasingly urgent. The stress condition of the rotor axial force in a dual-rotor turbine performance test specimen is as follows: Figure 2 As shown, the high-pressure turbine rotor experiences aerodynamic force in the rearward direction, and is also subjected to pressures Fa in the front chamber and Fb in the rear chamber of the high-pressure disk. Since Fa in the front chamber is greater than Fb in the rear chamber, the overall pressure in the high-pressure rotor disk is also rearward. Because the low-pressure guide vane 22 is located behind the high-pressure turbine rotor 21, the test requires simulating the airflow between high and low pressure. However, it is impossible to achieve axial force balance through a balancing bleed air system, resulting in excessive axial force on the high-pressure rotor and posing a safety hazard. The low-pressure turbine rotor 23 can introduce sealing gas in the rear chamber to balance the axial force, thus avoiding this problem. Summary of the Invention

[0005] The purpose of this application is to provide a rotor axial force adjustment structure for a dual-rotor turbine performance test piece to solve or alleviate at least one of the problems in the prior art.

[0006] The technical solution of this application is: a rotor axial force adjustment structure for a dual-rotor turbine performance test piece, comprising:

[0007] High-pressure turbine rotor disc assembly;

[0008] High-pressure turbine shaft connected to the high-pressure turbine rotor disk assembly;

[0009] A high-pressure gear coupling connected to the high-pressure turbine shaft, wherein a balance disc is connected to the high-pressure gear coupling; and

[0010] An intake bearing casing is provided, on which a second sealing ring and a first sealing ring connected to the second sealing ring are fixed. The first sealing ring, the second sealing ring, the balance disc, and the high-pressure gear coupling form a balance cavity with the high-pressure turbine shaft.

[0011] The first sealing ring is connected to an initiation pipe, through which balancing gas is introduced to form a balancing force acting on the balancing disc within the balancing chamber, thereby adjusting the axial force of the high-pressure turbine rotor.

[0012] In a preferred embodiment of this application, one side of the air intake tube is fixed with an air intake tube connector by welding, and the other side of the induction tube is fixed to the first sealing ring by a clamping nut that is threadedly connected to the air intake tube connector.

[0013] In a preferred embodiment of this application, a sealing gasket is provided between the clamping nut and the first sealing ring.

[0014] In a preferred embodiment of this application, the radial outer side of the balance disc is provided with balance disc grates, and the high-pressure sleeve gear coupling is provided with coupling grates. The parts of the first sealing ring that are adapted to the balance disc grates and the coupling grates are respectively provided with a first honeycomb and a second honeycomb. By the balance disc grates cooperating with the first honeycomb and the coupling grates cooperating with the second honeycomb, two grates-honeycomb sealing structures are formed in the balance cavity, thereby achieving the sealing of the balance cavity.

[0015] In a preferred embodiment of this application, the balance disc teeth are a three-stage stepped honeycomb.

[0016] In a preferred embodiment of this application, the balance disc and the high-pressure gear coupling are fitted with an interference fit.

[0017] In a preferred embodiment of this application, the second sealing ring is provided with an exhaust hole for venting the sealing air.

[0018] The axial force adjustment structure provided in this application features a balance disk cavity structure on the high-pressure turbine rotor, which solves the problem of excessive axial force on the high-pressure turbine rotor and ensures the safety of the dual-rotor test specimen. At the same time, through a reasonable rotor-stator connection structure design, it ensures a reasonable radial clearance between the rotor and stator during the operation of the test specimen, thus ensuring the pressure in the balance cavity. Attached Figure Description

[0019] 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.

[0020] Figure 1 This is a schematic diagram of the rotor axial force balance structure of a single-rotor turbine test piece in the prior art.

[0021] Figure 2 This is a schematic diagram of the rotor axial force balance structure for a dual-rotor turbine performance test specimen.

[0022] Figure 3 This is a schematic diagram of the rotor axial force adjustment structure of the dual-rotor turbine test piece of this application.

[0023] Figure 4 This is a schematic diagram of the rotor balance disk cavity structure of the dual-rotor turbine test piece of this application.

[0024] Figure label:

[0025] 100-Rotor Axial Force Adjustment Structure

[0026] 101-High Pressure Turbine Shaft

[0027] 102-High Pressure Turbine Rotor Disc Assembly

[0028] 103-High Pressure Gear Coupling

[0029] 104-Balance Disc

[0030] 105-Sealing Ring

[0031] 106-Air Draft Tube Connector

[0032] 107-Inhalation Tube

[0033] 108-Pivot Point Sealing Ring

[0034] 109-Intake bearing casing

[0035] 111-Self-locking bolt

[0036] 112-Self-locking nut

[0037] 113-First Honeycomb

[0038] 114 - First tooth

[0039] 115-Compression Nut

[0040] 116-Sealing Gasket

[0041] 117-Exhaust port

[0042] 118-Second Cell

[0043] 119 - Second tooth Detailed Implementation

[0044] 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.

[0045] To address the problem of excessive and unadjustable axial force on the high-pressure turbine rotor in dual-rotor turbine performance test specimens, this application combines the structural and stress characteristics of the high-pressure turbine rotor and designs a balance disk cavity structure on the high-pressure turbine rotor to solve the problem of excessive axial force on the high-pressure turbine rotor.

[0046] like Figure 3 and Figure 4 As shown, the rotor axial force adjustment structure of the dual-rotor turbine performance test piece provided in this application mainly consists of a high-pressure turbine shaft 101, a high-pressure turbine rotor disc assembly 102, a high-pressure gear coupling 103, a balance disc 104, a first sealing ring 105, an air intake pipe connector 106, an air intake pipe 107, a second sealing ring 108, and an intake bearing casing 109.

[0047] The high-pressure turbine rotor disc assembly 102 is connected to the right side of the high-pressure turbine shaft 101, the high-pressure gear coupling 103 is connected to the left side of the high-pressure turbine shaft 101, and the high-pressure gear coupling 103 is fixedly connected to the balance disc 104 by bolts 111 and self-locking nuts 112. The first sealing ring 105 is connected to the intake bearing casing 109 through the second sealing ring 108, so that the high-pressure gear coupling 103, the balance disc 104 and the first sealing ring 105 form a balance cavity structure at the front end of the high-pressure turbine rotor.

[0048] The air intake tube connector 106 is fixed to one side of the air intake tube 107 by welding. The other side of the air intake tube 107 is fixed to the first sealing ring 105 by a clamping nut 115 threadedly connected to the air intake tube connector 106. In some embodiments of this application, a sealing gasket 116 is provided between the clamping nut 115 and / or the air intake tube connector 106 and the first sealing ring 105 to achieve a seal between the air intake tube 105 and the first sealing ring 105.

[0049] In this application, the radial outer side of the balance disc 104 is provided with balance disc grates 114, and the part of the first sealing ring 105 that is adapted to the balance disc grates 114 is provided with a first honeycomb 113. At the same time, the high-pressure sleeve gear coupling 103 is provided with a coupling grates 119, and the lower part of the first sealing ring 105 is provided with a second honeycomb 118 adapted to the coupling grates 119. Through the cooperation of the balance disc grates 114 with the first honeycomb 113 and the coupling grates 119 with the second honeycomb 118, two grates-honeycomb sealing structures are formed in the balance cavity, thereby achieving the sealing of the balance cavity.

[0050] The balancing gas enters the balancing chamber from the air intake pipe 107. The pressure inside the balancing chamber acts forward in the direction of the balancing disk 104, thereby adjusting the axial force of the high-pressure turbine rotor.

[0051] Afterwards, the sealing bleed air is discharged from the balance chamber through the first honeycomb-grate sealing structure of the balance disc grates 114 and the first honeycomb 113, and then discharged to the outside of the engine. After being discharged from the balance chamber through the second honeycomb-grate sealing structure of the connecting grates 119 and the second honeycomb 118, it enters the rear cavity of the balance chamber and is discharged from the test piece through the exhaust port 117 on the second sealing ring 108.

[0052] In a preferred embodiment of this application, the balance disc teeth 114 of the balance disc 104 are three-step honeycomb to improve sealing ability and ensure that the pressure in the balance chamber remains at a reasonable level.

[0053] In a preferred embodiment of this application, the balance disc 104 and the high-pressure gear coupling 103 are fitted with an interference fit to reduce the change in the diameter of the comb teeth caused by the connection between rotors. Furthermore, the first sealing ring 105 is connected to the intake bearing casing 109 through the second sealing ring 108 (both are interference fits and screw connections) to achieve a stable connection of the stator components.

[0054] The axial force adjustment structure provided in this application features a balance disk cavity structure on the high-pressure turbine rotor, which solves the problem of excessive axial force on the high-pressure turbine rotor and ensures the safety of the dual-rotor test specimen. At the same time, through a reasonable rotor-stator connection structure design, it ensures a reasonable radial clearance between the rotor and stator during the operation of the test specimen, thus ensuring the pressure in the balance cavity.

[0055] 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 rotor axial force adjustment structure for a dual-rotor turbine performance test specimen, characterized in that, include: High-pressure turbine rotor disc assembly, low-pressure guide, and low-pressure turbine rotor; High-pressure turbine shaft connected to the high-pressure turbine rotor disk assembly; A high-pressure gear coupling connected to the high-pressure turbine shaft, wherein a balance disc is connected to the high-pressure gear coupling; and An intake bearing casing is provided, on which a second sealing ring and a first sealing ring connected to the second sealing ring are fixed. The first sealing ring, the second sealing ring, the balance disc, and the high-pressure gear coupling form a balance cavity with the high-pressure turbine shaft. The first sealing ring is connected to an air intake pipe. Balancing air is introduced through the air intake pipe to form a balancing force acting on the balancing disc within the balancing cavity, thereby adjusting the axial force of the high-pressure turbine rotor. The balancing disc has balancing disc grates on its radially outer side, and the high-pressure gear coupling has coupling grates. The parts of the first sealing ring that are adapted to the balancing disc grates and the coupling grates are respectively provided with a first honeycomb and a second honeycomb. By the balancing disc grates cooperating with the first honeycomb and the coupling grates cooperating with the second honeycomb, a two-grate-honeycomb sealing structure is formed in the balancing cavity, thereby achieving the sealing of the balancing cavity.

2. The rotor axial force adjustment structure for the dual-rotor turbine performance test specimen as described in claim 1, characterized in that, One side of the air intake tube is fixed with an air intake tube connector by welding, and the air intake tube is fixed to the first sealing ring by a compression nut that is threadedly connected to the air intake tube connector.

3. The rotor axial force adjustment structure for the dual-rotor turbine performance test specimen as described in claim 2, characterized in that, A sealing gasket is provided between the clamping nut and the first sealing ring.

4. The rotor axial force adjustment structure for the dual-rotor turbine performance test specimen as described in claim 1, characterized in that, The balance disc has a three-tiered honeycomb structure.

5. The rotor axial force adjustment structure for the dual-rotor turbine performance test specimen as described in claim 1, characterized in that, The balance disc and the high-pressure gear coupling are fitted with an interference fit.

6. The rotor axial force adjustment structure for the dual-rotor turbine performance test specimen as described in claim 1, characterized in that, The second sealing ring is provided with an exhaust hole for venting the sealing air.

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