Low-thermal-inertia pressure stabilization chamber structure for core machine table intake system

Abstract

The application discloses a low-thermal-inertia pressure stabilization chamber structure for a core machine table air inlet system, which comprises a pressure stabilization area, and the pressure stabilization area comprises an inner wall and an outer wall arranged outside the inner wall; wherein the thickness of the inner wall is 8mm-10mm, and an annular cavity is formed between the inner wall and the outer wall. The low-thermal-inertia pressure stabilization chamber structure for the core machine table air inlet system has the advantages that the inner wall has a relatively thin thickness, the heat capacity can be reduced, the wall surface temperature of the pressure stabilization chamber can quickly respond to the change of the air flow temperature, and the thermal inertia is reduced; in addition, the annular cavity is arranged to form a heat insulation layer, so that the heat loss of the high-temperature air flow in the pressure stabilization chamber to the external environment is reduced.

Description

Technical Field

[0001] This application relates to the field of aero-engine simulation testing, and more specifically, to a low thermal inertia pressure chamber structure for the intake system of a core engine. Background Technology

[0002] In a ground simulation test system for aero-engines, the pressure stabilizing chamber is a key device located between the air source and the engine under test. It is mainly used to stabilize and rectify the incoming airflow, so that the airflow pressure entering the engine is stable and evenly distributed, thereby meeting the requirements of engine testing for intake conditions.

[0003] Currently, pressure stabilizing chambers typically employ a single-layer thick-walled structure to meet structural strength and overall stability requirements. However, single-layer thick-walled structures exhibit significant thermal inertia. When intake air needs to be heated (e.g., during high-temperature testing), the thick metal walls absorb a large amount of heat as the high-temperature airflow passes through the pressure stabilizing chamber, resulting in significant heat loss. This not only increases the system's heating energy consumption but also negatively impacts the precise control of the intake air temperature. Specifically, the pressure stabilizing chamber wall acts as a "heat reservoir" with a large heat capacity, and its temperature response lags significantly behind changes in airflow temperature. This leads to dynamic deviations in the intake air temperature regulation process, reducing the sensitivity and accuracy of test parameter control, and consequently affecting the reliability of test data.

[0004] Therefore, how to provide a pressure stabilizing chamber structure with low thermal inertia and low heat loss has become a technical problem that needs to be solved in this field. Summary of the Invention

[0005] In view of this, this application proposes a low thermal inertia pressure stabilizing chamber structure for the core machine tool's air intake system. The thermal inertia is reduced by the design of the inner wall, and the heat loss of the low thermal inertia pressure stabilizing chamber structure is reduced by the design of the annular cavity.

[0006] According to this application, a low thermal inertia pressure stabilizing chamber structure for a core machine tool air intake system is proposed. The low thermal inertia pressure stabilizing chamber structure includes a pressure stabilizing area, which includes an inner wall and an outer wall disposed outside the inner wall. The thickness of the inner wall is 8mm-10mm, and an annular cavity is formed between the inner wall and the outer wall.

[0007] Preferably, the inner wall is provided with a through hole that penetrates the inner wall and the through hole communicates with the annular cavity.

[0008] Preferably, the diameter of the through hole is 5mm-20mm, and there are multiple through holes, with the opening rate of the through holes on the inner wall being 5%-15%.

[0009] Preferably, the outer wall of the pressure stabilizing zone in the low thermal inertia stabilizing chamber structure is provided with an air vent, which is connected to the outside and is used to maintain the pressure balance in the annular cavity.

[0010] Preferably, a plurality of stiffening plates are uniformly fixed between the inner wall and the outer wall in the annular cavity to improve the rigidity between the inner wall and the outer wall.

[0011] Preferably, the low thermal inertia stabilizing chamber structure further includes: an inlet area, which is cylindrical and disposed at the front end of the stabilizing chamber for allowing gas to enter the stabilizing chamber; an expansion area, which is disposed between the stabilizing chamber and the inlet area; and an outlet area, which is disposed at the rear end of the stabilizing chamber for allowing gas to exit the stabilizing chamber; wherein the inlet area and the expansion area are connected to the inner wall of the stabilizing chamber.

[0012] Preferably, the outlet area includes: a flow guide basin, the first end of which is funnel-shaped and passes through the inner wall of the voltage stabilizing area, and the second end of which is cylindrical and passes through the outer wall of the voltage stabilizing area; and a closed structure formed by the inner wall and the outer wall in the outlet area.

[0013] Preferably, the low thermal inertia stabilizing chamber structure is provided with a rectifier, which is disposed in the expansion zone and the stabilizing zone along the airflow direction; and a honeycomb unit is disposed in the stabilizing zone and is disposed downstream of the rectifier along the airflow direction.

[0014] Preferably, there are multiple rectifiers, and adjacent rectifiers divide the low thermal inertia stabilizing chamber structure into multiple transition sections; the honeycomb unit is arranged after the last rectifier along the airflow direction, and a static flow section is formed between the honeycomb unit and the stabilizing zone.

[0015] Preferably, the low thermal inertia stabilizing chamber structure further includes a heat insulation layer disposed on the outer surface of the low thermal inertia stabilizing chamber structure.

[0016] According to the low thermal inertia stabilizing chamber structure for the core machine tool intake system of this application, the inner wall has a relatively thin thickness, which can reduce the heat capacity and enable the stabilizing chamber wall temperature to respond quickly to changes in airflow temperature, thereby reducing thermal inertia; secondly, the annular cavity is set to form a heat insulation layer, thereby reducing the heat loss of high-temperature airflow in the stabilizing chamber to the external environment.

[0017] Other features and advantages of this application will be described in detail in the following detailed description section. Attached Figure Description

[0018] The accompanying drawings, which form part of this application, are used to provide a further understanding of this application, and the illustrative embodiments and descriptions thereof are used to explain this application. In the drawings: Figure 1 This is a structural schematic diagram of the low thermal inertia stabilizing chamber structure according to this application.

[0019] Figure 2 This is a cross-sectional schematic diagram of the low thermal inertia stabilizing chamber structure according to this application.

[0020] Figure 3 This is a schematic diagram of the internal cavity of the low thermal inertia stabilizing chamber structure according to this application. Detailed Implementation

[0021] The technical solution of this application will now be described in detail with reference to the accompanying drawings and embodiments.

[0022] According to this application, such as Figures 1-3 As shown, a low thermal inertia pressure stabilizing chamber structure for the air intake system of a core machine tool is proposed. The low thermal inertia pressure stabilizing chamber structure includes a pressure stabilizing region 1, which includes an inner wall 11 and an outer wall 12 disposed outside the inner wall 11. The thickness of the inner wall 11 is 8mm-10mm, and an annular cavity is formed between the inner wall 11 and the outer wall 12.

[0023] To ensure the structural strength and stability of the low thermal inertia pressure stabilizing chamber structure, a single-layer thick-walled structure is traditionally used. However, this type of structure results in significant thermal inertia and heat loss. In this application, a double-layer structure of inner wall 11 and outer wall 12 is adopted. The inner wall 11 has a thinner thickness, and the outer wall 12 can also have a thinner structure than the traditional single-layer thick-walled structure. The thickness of the inner wall 11 can be 8mm-10mm. The thickness of the inner wall 11 and outer wall 12 is determined according to the working pressure and operating temperature of the low thermal inertia pressure stabilizing chamber structure, and the preferred material is stainless steel or high-temperature alloy.

[0024] The aforementioned inner wall 11 and outer wall 12 allow the high-temperature airflow to reduce its heat capacity and thermal inertia as it flows through the pressure stabilization zone 1. This enables the wall temperature of the low thermal inertia pressure stabilization chamber structure to quickly follow the temperature changes of the airflow, thereby reducing the lag in temperature control and facilitating more precise temperature control, thus improving the reliability of the experiment. Secondly, it also reduces the heat loss of the low thermal inertia pressure stabilization chamber structure, thereby reducing the operating cost of the experiment.

[0025] The radial cross-section of the aforementioned pressure stabilizing zone 1 is annular, and the distance between the inner wall 11 and the outer wall 12 is 60mm-120mm to form an annular cavity. The aforementioned annular cavity forms a heat insulation layer in the pressure stabilizing zone 1, which can significantly reduce the heat loss of high-temperature airflow to the external environment.

[0026] To further reduce heat loss, preferably, the inner wall 11 may be provided with a through hole 13 that penetrates the inner wall 11 and communicates with the annular cavity. The outer wall 12 of the pressure stabilizing zone 1 in the low thermal inertia stabilizing chamber structure is provided with a vent 14 that communicates with the outside and is used to maintain the pressure balance in the annular cavity. The vent 14 is connected to the outside through a pipe. On the one hand, it can remove some of the heat absorbed by the inner wall 11, and on the other hand, it can form a temperature buffer zone in the annular cavity, thereby reducing the heat lost to the outside environment through the outer wall 12.

[0027] In a preferred embodiment, the diameter of the through hole 13 is 5mm-20mm, which can be selected according to actual needs; and there are multiple through holes 13, which are evenly distributed on the surface of the inner wall 11. The opening rate of the through holes 13 on the inner wall 11 is 5%-15%, which can ensure sufficient air passage between the inner wall 11 and the annular cavity, and can also avoid the through holes 13 from affecting the structural strength of the inner wall 11. The specific value is determined according to the maximum working condition of the test.

[0028] To enable airflow into the pressure stabilizing chamber and to supply the airflow into the pressure stabilizing chamber to the engine, the low thermal inertia pressure stabilizing chamber structure may further include: an inlet region 2, which may be cylindrical and located at the front end of the pressure stabilizing region 1, for allowing gas to enter the pressure stabilizing region 1; and an expansion region 3, located between the pressure stabilizing region 1 and the inlet region 2. The expansion region 3 is trapezoidal along the axial direction of the low thermal inertia pressure stabilizing chamber structure, with the width of the top end of the trapezoid being the same as the diameter of the inlet region 2 and the width of the bottom end being the same as the width of the pressure stabilizing region 1. This allows the high-pressure airflow in the inlet region 2 to decelerate and increase pressure during expansion and to be evenly distributed, converting dynamic pressure into static pressure. In addition, it can suppress flow separation and the generation of eddies, thereby improving the uniformity and stability of the airflow entering the pressure stabilizing region 1. The inlet area 2 and the expansion area 3 are connected to the inner wall 11 of the pressure stabilizing area 1. The connection method can be either a seamless integral connection structure or a flange connection, which can be selected according to actual needs to ensure the continuity of the airflow passage area, avoid local disturbances to the airflow caused by the low thermal inertia pressure stabilizing chamber structure, and thus further improve the stability of the airflow and the pressure stabilizing effect.

[0029] The wall of the aforementioned expansion zone and the structural axis of the low thermal inertia stabilizing chamber can be at an appropriate angle, which is determined based on the aerodynamic profile design of the low thermal inertia stabilizing chamber structure and the specific test conditions.

[0030] An outlet zone 4 is located at the rear end of the pressure stabilizing zone 1 and is used to discharge the gas from the pressure stabilizing zone 1. Preferably, the outlet zone 4 includes a guide basin 41, the first end of which is flared and passes through the inner wall 11 of the pressure stabilizing zone 1, and the second end is cylindrical and passes through the outer wall 12 of the pressure stabilizing zone 1. The guide basin 41 adopts a double-hinged profile and can guide the airflow in the pressure stabilizing zone 1. The flared first end forms a curved transition to suppress flow separation and uniform airflow velocity, while reducing local resistance loss and pressure fluctuations in the outlet zone 4, so that the airflow is provided to the engine in a stable, uniform, and low-disturbance state. A closed structure 42 is formed in the outlet zone 4 by the inner wall 11 and the outer wall 12. A closed structure 42 is provided between the connection between the above-mentioned flow guide basin 41 and the inner wall 11 and the outer wall 12. A heat insulation layer can be provided at the connection to increase thermal resistance, reduce heat conduction to the outer wall 12, reduce thermal inertia and thermal stress concentration, thereby improving the reliability of the low thermal inertia stabilizing chamber structure.

[0031] To further improve the stability and uniformity of the airflow before it enters the engine, preferably, a rectifier 5 can be provided within the low thermal inertia stabilizing chamber structure. This rectifier 5 is positioned along the airflow direction within the expansion zone 3 and the stabilizing zone 1. The rectifier 5 can have an appropriate shape, such as a rectifier mesh. The airflow entering the low thermal inertia stabilizing chamber structure often exhibits flow deviation or vortices. The rectifier 5 can divide and constrain the airflow to flow axially, thereby eliminating vortices and lateral velocity components, reducing turbulence intensity, weakening pressure pulsations, and improving airflow uniformity and stability. Preferably, there are multiple rectifiers 5, including a honeycomb unit 6, which is positioned within the stabilizing zone 1 and downstream of the rectifier 5 along the airflow direction. The honeycomb unit 6 is positioned after the last rectifier 5 along the airflow direction, and a stabilization section 61 is formed between the honeycomb unit 6 and the stabilizing zone 1. The rectifier 5 divides the low thermal inertia stabilizing chamber structure into multiple transition sections 51. During the multi-stage rectification process, the airflow gradually weakens the turbulence and lateral velocity components, while the flow is restored in the transition section 51. The honeycomb unit 6 can further constrain the airflow along the axial direction, and the static flow section 61 can eliminate the outlet disturbance of the stabilizing zone 1 to further obtain a uniform and stable airflow. This can improve the flow stabilization effect and test accuracy of the low thermal inertia stabilizing chamber structure, thereby improving the reliability of the test results.

[0032] To enhance the structural strength of the low thermal inertia stabilizing chamber, preferably, multiple stiffening ribs 15 are uniformly fixed between the inner wall 11 and the outer wall 12 within the annular cavity to improve the rigidity between them. The stiffening ribs 15 can be fixed to the inner wall 11 and the outer wall 12 by welding or bolting. The stiffening ribs 15 can be spaced appropriately, for example, with an axial spacing of 500mm-800mm, which can be selected according to actual needs. The stiffening ribs 15 ensure the overall rigidity and stability of the inner wall 11 and the outer wall 12, thereby overcoming the vulnerability of thin-walled structures to vibration.

[0033] To further reduce heat loss, preferably, the low thermal inertia stabilizing chamber structure may also include a thermal insulation layer disposed on the outer surface of the low thermal inertia stabilizing chamber structure. The material of the thermal insulation layer may be ceramic fiber blanket or rock wool.

[0034] The preferred embodiments of this application have been described in detail above. However, this application is not limited to the specific details of the above embodiments. Within the scope of the technical concept of this application, various simple modifications can be made to the technical solution of this application, and these simple modifications all fall within the protection scope of this application.

[0035] It should also be noted that the various specific technical features described in the above embodiments can be combined in any suitable manner without contradiction. In order to avoid unnecessary repetition, this application will not describe the various possible combinations separately.

[0036] Furthermore, various different embodiments of this application can be combined in any way, as long as they do not violate the spirit of this application, they should also be regarded as the content disclosed by this invention.

Claims

1. A low thermal inertia pressure stabilizing chamber structure for the intake system of a core machine tool, characterized in that, The low thermal inertia pressure stabilizing chamber structure includes a pressure stabilizing zone (1), which includes an inner wall (11) and an outer wall (12) disposed outside the inner wall (11). The thickness of the inner wall (11) is 8mm-10mm, and an annular cavity is formed between the inner wall (11) and the outer wall (12).

2. The low thermal inertia pressure stabilizing chamber structure for the core machine tool intake system according to claim 1, characterized in that, The inner wall (11) is provided with a through hole (13) that penetrates the inner wall (11), and the through hole (13) communicates with the annular cavity.

3. The low thermal inertia pressure stabilizing chamber structure for the core machine tool intake system according to claim 2, characterized in that, The diameter of the through hole (13) is 5mm-20mm, and there are multiple through holes (13). The opening rate of the through holes (13) on the inner wall (11) is 5%-15%.

4. The low thermal inertia pressure stabilizing chamber structure for the core machine tool intake system according to claim 2, characterized in that, The outer wall (12) of the pressure stabilizing zone (1) in the low thermal inertia stabilizing chamber structure is provided with an air vent (14), which is connected to the outside and is used to maintain the pressure balance in the annular cavity.

5. The low thermal inertia pressure stabilizing chamber structure for the core machine tool intake system according to claim 1, characterized in that, Multiple stiffening plates (15) are uniformly fixed between the inner wall (11) and the outer wall (12) in the annular cavity to improve the rigidity between the inner wall (11) and the outer wall (12).

6. The low thermal inertia pressure stabilizing chamber structure for the core machine tool intake system according to claim 1, characterized in that, The low thermal inertia pressure stabilizing chamber structure also includes: Inlet area (2), which is cylindrical, is located at the front end of the pressure stabilizing area (1) and is used to allow gas to enter the pressure stabilizing area (1). An expansion region (3) is provided between the voltage stabilizing region (1) and the inlet region (2); The outlet area (4) is located at the rear end of the pressure stabilizing area (1) and is used to discharge the gas from the pressure stabilizing area (1); The inlet area (2) and the expansion area (3) are connected to the inner wall (11) of the voltage stabilizing area (1).

7. The low thermal inertia pressure stabilizing chamber structure for the core machine tool intake system according to claim 6, characterized in that, The export zone (4) includes: The flow guide basin (41) has a first end that is horn-shaped and passes through the inner wall (11) of the voltage stabilizing zone (1), and a second end that is cylindrical and passes through the outer wall (12) of the voltage stabilizing zone (1). A closed structure (42) is formed in the outlet area (4) by the inner wall (11) and the outer wall (12).

8. The low thermal inertia pressure stabilizing chamber structure for the core machine tool intake system according to claim 6, characterized in that, The low thermal inertia stabilizing chamber structure is equipped with a rectifier (5), which is located in the expansion zone (3) and the stabilizing zone (1) along the airflow direction; A cell (6) is disposed within the voltage stabilization zone (1) and is disposed downstream of the rectifier (5) along the airflow direction.

9. The low thermal inertia pressure stabilizing chamber structure for the core machine tool intake system according to claim 8, characterized in that, The number of rectifiers (5) is multiple, and the adjacent rectifiers (5) divide the low thermal inertia stabilizing chamber structure into multiple transition sections (51). The honeycomb unit (6) is positioned after the last rectifier (5) along the airflow direction, and a static flow section (61) is formed between the honeycomb unit (6) and the voltage stabilization zone (1).

10. The low thermal inertia pressure stabilizing chamber structure for the core machine tool intake system according to any one of claims 1-9, characterized in that, The low thermal inertia stabilizing chamber structure also includes a thermal insulation layer disposed on the outer surface of the low thermal inertia stabilizing chamber structure.

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