Experimental component with an annular cavity structure for simulating the leakage flow at the root of the rotor blades of a compression component

Abstract

The present invention provides an annular cavity structure test piece for simulating the leakage flow of the rotor blade root of a compression component, comprising: a rotor assembly including a first stepped surface and a second stepped surface arranged at intervals; an inner air supply ring, with a first mating gap provided between one end and the first stepped surface, and a sealing labyrinth tooth arranged in the first mating gap; an inner ring, with a second mating gap provided between one end and the second stepped surface, and a simulated leakage labyrinth tooth arranged in the second mating gap, and an air supply annular cavity formed between the inner air supply ring and the inner ring; an air supply assembly communicated with the air supply annular cavity; a compressor flow passage arranged outside the inner air supply ring and communicated with the air supply annular cavity through the second mating gap, and a working measurement assembly arranged in the compressor flow passage. The embodiment of the present invention can provide a stable air supply flow rate with stable flow and pressure for the blade root to simulate the root flow leakage conditions under different states.

Description

Technical Field

[0001] The present invention relates to the technical field of aeroengines, and particularly to an annular cavity structure test piece for simulating the leakage flow of the rotor blade root of a compression component. Background Art

[0002] An adaptive cycle engine is a variable cycle engine that can achieve adaptive adjustment through a control system according to flight missions and states. By changing geometric adjustment to change engine operating parameters such as pressure ratio, turbine inlet temperature, air flow rate, and bypass ratio, etc., the engine shows excellent performance in various flight environments. It inherits the structural characteristics of the variable cycle engine, can achieve a larger range of bypass ratio adjustment and optimization, and has a better mission adaptability than the double bypass variable cycle engine.

[0003] With the development of variable cycle and adaptive engine technologies, more bypasses are required to adapt to the changes in flow rate and pressure ratio under different working conditions. In addition to the two bypasses in the conventional scheme to adjust the flow rate, an additional bypass (the third bypass) is needed to be suitable for a wider working range to meet the higher requirements of the engine, with a Flade fan. The working environment of the Flade fan is different from that of the conventional fan. The main manifestation is that as the rotational speed increases, the pressure at the tip of the main fan rotor blade rises relatively fast, while the pressure at the root of the Flade fan rotor blade rises relatively slow, resulting in a pressure difference. The high-pressure gas in the B flow path of the main fan will leak from the sealing part to the root of the Flade fan A along paths I and II. The leakage flow rate will disturb the gas at the inlet edge and exhaust edge of the Flade fan A. The changing flow rate at the inlet and outlet will also affect the performance of the Flade fan A. The leakage flow rate changes with the different pressure differences.

[0004] In order to verify the influence of the root leakage flow on the fan performance under different states, a continuously adjustable air supply structure needs to be designed. The air supply structure can provide a stable air supply flow rate with stable flow rate and pressure for the blade root to simulate the root flow leakage situation under different states. Summary of the Invention

[0005] In view of this, an embodiment of this specification provides an annular cavity structure test piece for simulating the leakage flow of the rotor blade root of a compression component to simulate the root flow leakage situation under different states.

[0006] The embodiments of this specification provide the following technical solutions: A test piece with an annular cavity structure for simulating the leakage flow at the root of the rotor blade of a compression component, comprising: a rotor assembly including a first step surface and a second step surface arranged at intervals; an inner supply air ring, with a first fitting gap provided between one end and the first step surface, and a sealing labyrinth provided in the first fitting gap; an inner ring, with a second fitting gap provided between one end and the second step surface, and a simulated leakage labyrinth provided in the second fitting gap, and a supply air ring cavity formed between the inner supply air ring and the inner ring; a supply air assembly communicating with the supply air ring cavity; a compressor flow passage provided outside the inner supply air ring and communicating with the supply air ring cavity through the second fitting gap, and a working measurement assembly provided in the compressor flow passage.

[0007] Further, the number of labyrinth teeth of the sealing labyrinth is greater than the number of labyrinth teeth of the simulated leakage labyrinth, and the gap between the sealing labyrinth and the inner supply air ring is smaller than the gap between the simulated leakage labyrinth and the inner ring.

[0008] Further, the inner supply air ring includes a mixing section, a transition section, and a pressure equalizing section connected in sequence along the gas flow direction. Both the mixing section and the pressure equalizing section are cylindrical sections. The longitudinal section of the transition section is conical, and the large diameter end of the transition section is connected to the end of the mixing section, and the small diameter end of the transition section is connected to the beginning of the pressure equalizing section.

[0009] Further, pressure measurement holes are provided on the pressure equalizing section, and pressure measuring tubes are provided in the pressure measurement holes.

[0010] Further, the supply air assembly includes multiple supply air pipelines, and the multiple supply air pipelines are evenly spaced circumferentially along the supply air ring cavity.

[0011] Further, the inner supply air ring, the inner ring, the supply air assembly, and the compressor flow passage together form a measurement unit. The test piece with an annular cavity structure for simulating the leakage flow at the root of the rotor blade of a compression component includes two measurement units, and the two measurement units are symmetrically arranged on both sides of the rotor assembly.

[0012] Compared with the prior art, the above at least one technical solution adopted in the embodiments of this specification can achieve at least the following beneficial effects: By adding a supply air ring cavity structure at the root of the rotor blade, the present invention simulates the flow leakage at the root of the fan / compressor rotor blade. Through the refined design of the supply air ring cavity structure, a uniform and stable cavity pressure is formed in the cavity. During the test, by continuously adjusting the cavity pressure, the influence of different leakage amounts on the fan performance can be obtained. Description of the Drawings

[0013] In order to more clearly illustrate the technical solutions of the embodiments of this application, the following will briefly introduce the drawings required in the embodiments. Obviously, the drawings described below are only some embodiments of this application. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.

[0014] Figure 1 is the overall assembly schematic diagram of the embodiment of the present invention;

[0015] Figure 2 is Figure 1 a partial enlarged view of;

[0016] Figure 3 is the structural schematic diagram of the rotor assembly;

[0017] Figure 4 is the structural schematic diagram of the inner gas supply ring.

[0018] In the figure, the reference numerals are: 7, inlet casing; 8, gas supply pipe; 9, inner ring; 13, inlet adjustable vane; 15, rotor assembly; 16, inner gas supply ring; 161, mixing section; 162, transition section; 163, pressure equalizing section; 164, pressure measurement hole; 18, pressure measuring pipe; 20, simulated leakage grate teeth; 22, sealing grate teeth; 101, gas supply hole; 102, gas supply pipe; 103, mixing cavity; 104, transition cavity; 105, pressure equalizing cavity. Detailed Embodiments

[0019] The embodiments of the present application will be described in detail below with reference to the accompanying drawings.

[0020] It should be noted that, without conflict, the embodiments in the present application and the features in the embodiments may be combined with each other. The present invention will be described in detail below with reference to the accompanying drawings and in conjunction with the embodiments.

[0021] As Figures 1 to 4 shown, the embodiment of the present invention provides a ring cavity structure test piece for simulating the leakage flow of the rotor blade root of a compression component, including a rotor assembly 15, an inner gas supply ring 16, an inner ring 9, a gas supply assembly, and a compressor flow passage. The rotor assembly 15 includes a first stepped surface and a second stepped surface arranged at intervals; a first mating gap is provided between one end of the inner gas supply ring 16 and the first stepped surface, and sealing grate teeth 22 are arranged in the first mating gap; a second mating gap is provided between one end of the inner ring 9 and the second stepped surface, and simulated leakage grate teeth 20 are arranged in the second mating gap, and a gas supply ring cavity is formed between the inner gas supply ring 16 and the inner ring 9; the gas supply assembly is communicated with the gas supply ring cavity; the compressor flow passage is arranged outside the inner gas supply ring 16 and is communicated with the gas supply ring cavity through the second mating gap, and a working measurement assembly is arranged in the compressor flow passage.

[0022] The present invention simulates the flow leakage at the root of the fan / compressor rotor blade by adding a gas supply ring cavity structure at the root of the rotor blade. Through the refined design of the gas supply ring cavity structure, a uniform and stable cavity pressure is formed in the ring cavity. During the test, by continuously adjusting the cavity pressure, the influence of different leakage amounts on the fan performance is obtained.

[0023] The number of teeth of the sealing labyrinth teeth 22 is greater than that of the simulated leakage labyrinth teeth 20, and the gap between the sealing labyrinth teeth 22 and the inner air supply ring 16 is smaller than the gap between the simulated leakage labyrinth teeth 20 and the inner ring 9.

[0024] In the embodiment of the present invention, a better sealing effect can be achieved through a larger number of labyrinth teeth and a smaller gap between the labyrinth teeth, ensuring the establishment of pressure in the annular cavity. The number of teeth and the gap of the simulated sealing labyrinth teeth 22 and the simulated leakage labyrinth teeth 20 in different states are calculated to adjust the pressure in the annular cavity, so as to simulate the leakage situation at the root of the fan under different working conditions.

[0025] The inner air supply ring 16 includes a mixing section 161, a transition section 162, and a pressure equalizing section 163 that are connected in sequence along the gas flow direction. Both the mixing section 161 and the pressure equalizing section 163 are cylindrical sections. The longitudinal section of the transition section 162 is conical, and the large diameter end of the transition section 162 is connected to the end of the mixing section 161, and the small diameter end of the transition section 162 is connected to the head end of the pressure equalizing section 163.

[0026] By adding the structures of the mixing section 161, the transition section 162, and the pressure equalizing section 163 in the inner air supply ring 16, the gas provided by the test bench is fully mixed in the air supply cavity, forming a uniform and stable leakage air flow, improving the measurement accuracy and increasing the coincidence degree of the test and the design.

[0027] A pressure measurement hole 164 is provided on the pressure equalizing section 163 for installing a pressure measuring tube 18 to measure the air supply pressure.

[0028] It should be noted that the rotor assembly 15, the inner air supply ring 16, and the inner ring 9 together form a front air supply annular cavity. The front air supply annular cavity consists of three parts: a mixing cavity 103, a transition cavity 104, and a pressure equalizing cavity 105. The mixing cavity 103 is used for mixing the air flow in the air supply pipe, the transition cavity 104 is used for smooth transition, and the pressure equalizing cavity 105 is used for stabilizing the air supply pressure.

[0029] The air supply assembly includes a plurality of air supply pipelines, and the plurality of air supply pipelines are circumferentially and evenly distributed along the air supply annular cavity.

[0030] In the embodiment of the present invention, air supply is carried out through a test bench. At the front end, through the air supply hole 101 and the air supply pipe 102 of the inlet casing 7, the front edge LE root of the rotor blade is supplied with air through the mixing cavity 103, the transition cavity 104, and the pressure equalizing cavity 105.

[0031] It should be noted that a compressor flow passage is formed between the inner ring 9 and the inlet casing 7, and an inlet adjustable vane 13 is also provided in the compressor flow passage.

[0032] The air supply inner ring 16, the inner ring 9, the air supply assembly and the compressor flow path together form a measurement unit. The annular cavity structure test piece that simulates the root leakage flow of the rotor blades of the compression component includes two measurement units. The two measurement units have the same or similar structures and are symmetrically arranged on both sides of the rotor assembly 15.

[0033] In the embodiment of the present invention, the front and rear air supply chamber pressures are independent of each other, and the air supply pressure is continuously variable during the test. By separately controlling the pressure value of the air supply chamber during the test, different root leakage flows can be obtained.

[0034] As described above, only the specific embodiments of the present invention are provided, and the scope of the invention implementation cannot be limited by them. Therefore, the replacement of equivalent components or the equivalent changes and modifications made according to the protection scope of the present invention patent should still fall within the scope covered by this patent. In addition, the technical features in the present invention can be freely combined with each other between technical features, between technical features and technical solutions, and between technical solutions.

Claims

1. A test piece of an annular cavity structure for simulating the leakage flow at the root of the rotor blade of a compression component, characterized in that Comprising: A rotor assembly (15) including a first stepped surface and a second stepped surface arranged at intervals; An inner air supply ring (16), with a first fitting clearance provided between one end and the first stepped surface, and a sealing labyrinth (22) arranged in the first fitting clearance; An inner ring (9), with a second fitting clearance provided between one end and the second stepped surface, and a simulated leakage labyrinth (20) arranged in the second fitting clearance, and an air supply ring cavity formed between the inner air supply ring (16) and the inner ring (9); An air supply assembly communicating with the air supply ring cavity; A compressor flow passage arranged outside the inner air supply ring (16) and communicating with the air supply ring cavity through the second fitting clearance, and a working measurement assembly arranged in the compressor flow passage; The number of labyrinths of the sealing labyrinth (22) is greater than that of the simulated leakage labyrinth (20), and the clearance between the sealing labyrinth (22) and the inner air supply ring (16) is smaller than the clearance between the simulated leakage labyrinth (20) and the inner ring (9); The inner air supply ring (16) includes a mixing section, a transition section, and a pressure equalizing section connected in sequence along the gas flow direction. Both the mixing section and the pressure equalizing section are cylindrical sections. The longitudinal section of the transition section is conical, and the large diameter end of the transition section is connected to the end of the mixing section, and the small diameter end of the transition section is connected to the beginning of the pressure equalizing section; The inner air supply ring (16), the inner ring (9), the air supply assembly, and the compressor flow passage together form a measurement unit. The ring cavity structure test piece for simulating the leakage flow of the rotor blade root of the compression component includes two such measurement units, and the two measurement units are symmetrically arranged on both sides of the rotor assembly (15).

2. The annular cavity structure test piece for simulating the leakage flow of the rotor blade root of the compression component according to claim 1, characterized in that, Pressure measurement holes are provided on the pressure equalizing section, and pressure measuring tubes are arranged in the pressure measurement holes.

3. The annular cavity structure test piece for simulating the leakage flow of the rotor blade root of the compression component according to claim 1, characterized in that, The air supply assembly includes a plurality of air supply pipelines, and the plurality of air supply pipelines are circumferentially and evenly distributed along the air supply ring cavity.

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