An air intake device for a gas turbine

Abstract

This disclosure relates to the field of aviation or civil auxiliary power unit / starter technology, and particularly to an air intake device for a gas turbine. In the prior art, during load-section flow control, when the inlet guide vanes are closed to their minimum, the compressor flow in the load section cannot be zero; otherwise, the compressor will flutter, potentially leading to compressor damage. However, the inherent clearance fit of this device allows air to flow into the load compressor through the gaps in the grille even when the load intake grille or mesh channel is completely closed, preventing a complete lack of flow and successfully avoiding potential flutter problems in the load compressor. Furthermore, under non-design operating conditions, the grille-type intake airflow is more uniform in the circumferential direction, while traditional compressors with guide vanes, due to separation on the guide vanes, generate uneven circumferential excitation sources, leading to blade vibration problems.

Description

TECHNICAL FIELD

[0001] The present disclosure relates to the field of aviation or civil auxiliary power unit / starter, in particular to an air intake device of a gas turbine. BACKGROUND

[0002] The auxiliary power unit with double side air intake, one side is arranged with a centrifugal compressor, called load compressor, mainly responsible for air induction and power generation, the other side is arranged with a conventional turbine engine, called power section, responsible for output power. When the aircraft does not need air induction and power generation, the load section can not work, at this time the conventional load section compressor is closed by adjusting the angle of the radial or axial inlet guide vane arranged at the front end of the load compressor, so that the inlet flow of the load compressor is close to zero, at this time the load compressor does not consume the power output by the power section, so that the power section can output more power for the aircraft to use.

[0003] The existing load compressor flow axial or radial control device is usually controlled by a hydraulic actuator to control the movement of the connecting rod connected to the guide vane, thereby rotating the axial or radial guide vane to achieve the purpose of controlling the flow of the load compressor. Due to the inherent characteristics of the structure, the accuracy of the guide vane angle adjustment is not high. Since the force of the actuator cylinder is converted through multiple channels, and there are dozens of groups of axial or radial guide vanes, it is easy to cause inconsistent rotation of the guide vane angle or guide vane not following during the adjustment process, resulting in control failure. In addition, since the guide vane is in the main flow, the blade thickness is usually thin, and the guide vane as a thin cantilever mechanism is prone to breakage failure under the impact of long-term high-speed airflow and external objects. Furthermore, due to the inevitable separation of the blade surface, it will cause uneven circumferential airflow, causing circumferential disturbance to the impeller and causing vibration problems. SUMMARY

[0004] In view of the above problems, the present disclosure provides an air intake device of a gas turbine.

[0005] An air intake device of a gas turbine, comprising an air intake device,

[0006] The air intake device comprises a load section arranged with a centrifugal compressor and a power section arranged with a turbine engine; the load section is used for air induction and power generation; the power section is used for output power;

[0007] The load section and the power section are separately inhaled; the intake adopts a push-pull type flow control structure;

[0008] When air induction and power generation are not needed, the load section stops working, and the load section intake passage is closed by adjusting the flow control structure.

[0009] Further, the push-pull type flow control structure comprises a fence or a grid.

[0010] Furthermore, the fences of the load section are fixed, while the fences of the power section are interspersed and staggered with those of the load section.

[0011] Furthermore, the power section fence has at least two layers.

[0012] Furthermore, the power section fence has two layers.

[0013] Furthermore, the upper layer of the power section fence can slide left and right, and ball bearings or rollers are installed between the two layers of fences or grilles.

[0014] Furthermore, the flow control structure is controlled hydraulically.

[0015] This disclosure has at least the following advantages compared to the prior art:

[0016] This disclosure has a simple structure and does not require a complex mechanism similar to guide vane adjustment; it only requires an axial actuation device.

[0017] Since the strength of the air intake mesh is sufficient to meet the usage requirements, the fence disclosed herein can also be made as thin as the air intake mesh, greatly reducing the overall weight while still maintaining the function of the air intake mesh.

[0018] This disclosure can be coupled with the air intake grille design to reduce the total number of parts;

[0019] This disclosure uses hydraulic or other motion control structures for direct control. The motion of the control mechanism and the motion of the fence exhibit a simple linear relationship, resulting in high control precision and resistance to control failure.

[0020] Theoretically, the thickness of the fence (along the flow direction) is not limited by this disclosure, there will be no strength problem, and it has a stronger resistance to damage from external objects;

[0021] The structure of the air intake grille itself determines that it can also play a certain role in preventing foreign objects from being sucked in;

[0022] In existing technologies, during the flow control process in the load section, when the inlet guide vanes are closed to the minimum, the compressor flow in the load section cannot be zero; otherwise, the compressor will flutter, which can lead to compressor damage in severe cases. However, due to the inherent clearance fit of this engine's structure, even when the load inlet grille or mesh channel is completely closed, air can still flow into the load compressor through the gaps in the grille, preventing the compressor from having no flow at all and successfully avoiding the possible flutter problem of the load compressor.

[0023] Under non-design conditions, the airflow of the grille-type intake is more uniform in the circumferential direction, while the traditional compressor with guide vanes will generate an uneven circumferential excitation source due to the separation on the guide vanes, resulting in blade vibration problems.

[0024] Other features and advantages of this disclosure will be set forth in the following description and will be apparent in part from the description or may be learned by practicing the disclosure. The objects and other advantages of this disclosure may be realized and obtained by means of the structures pointed out in the description and the accompanying drawings. Attached Figure Description

[0025] To more clearly illustrate the technical solutions in the embodiments of this disclosure or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of this disclosure. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0026] Figure 1 An auxiliary power unit air intake duct for dual-sided object air intake in an embodiment of this disclosure;

[0027] Figure 2 This illustration shows the barrier-type channel fully open, half open, and fully closed according to embodiments of this disclosure. Figure 1 ;

[0028] Figure 3 This diagram illustrates the fully open, partially open, and fully closed configurations of the grille-type channel according to embodiments of this disclosure. Figure 2 ;

[0029] Figure 4 This is a three-dimensional schematic diagram of the fully open fence-type passage according to an embodiment of the present disclosure;

[0030] Figure 5 This is a three-dimensional schematic diagram of the fence-type passage in a half-open state according to an embodiment of this disclosure;

[0031] Figure 6 This is a three-dimensional schematic diagram of the fully closed gate-type passage according to an embodiment of the present disclosure;

[0032] Figure 7 This is a three-dimensional schematic diagram of the fully open grid-type channel according to an embodiment of the present disclosure;

[0033] Figure 8 This is a three-dimensional schematic diagram of the grid-type channel in a semi-open state according to an embodiment of this disclosure;

[0034] Figure 9 This is a three-dimensional schematic diagram of the fully closed grid-type channel according to an embodiment of the present disclosure. Detailed Implementation

[0035] To make the objectives, technical solutions, and advantages of the embodiments of this disclosure clearer, the technical solutions of the embodiments of this disclosure will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this disclosure, and not all embodiments. Based on the embodiments of this disclosure, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this disclosure.

[0036] In the field of aero-engines, auxiliary power units with dual opposing air intakes consist of a centrifugal compressor on one side, called the load compressor, which is primarily responsible for bleed air and power generation. The other side houses a conventional turbine engine, called the power section, which is responsible for power output. When the aircraft does not require bleed air or power generation, the load section can be inactive. In this case, the conventional load section compressor closes its intake passage by adjusting the angle of the radial or axial inlet guide vanes at its front end, bringing the inlet flow rate close to zero. Since the load compressor does not consume power from the power section, the power section can output more power for the aircraft.

[0037] In existing technologies, conventional axial or radial flow control devices for load compressors typically use hydraulic actuators to control the movement of connecting rods linking to the guide vanes, thereby rotating the axial or radial guide vanes to control the flow rate of the load compressor. Due to the inherent characteristics of the structure, the guide vane angle adjustment accuracy is not high. Because the force of the actuator undergoes multiple conversions, and there are often dozens of sets of axial or radial guide vanes, inconsistent guide vane angle rotation or guide vane non-following phenomena are prone to occur during adjustment, leading to control failure. Furthermore, since the guide vanes are located in the main flow path, their blade thickness is often relatively thin. As thin cantilever mechanisms, guide vanes are highly susceptible to breakage under long-term high-speed airflow and external impacts. Moreover, the unavoidable separation on the blade surface causes circumferential airflow unevenness, resulting in circumferential disturbance to the impeller and causing vibration problems.

[0038] Therefore, this disclosure proposes an air intake device for a gas turbine.

[0039] The technical problem to be solved by this disclosure is: a new type of load compressor flow control device that is convenient and highly accurate, with high reliability; and a solution to the problem of circumferential non-uniformity of inlet airflow caused by the presence of guide vanes, so as to avoid vibration failure.

[0040] like Figure 1 As shown, an air intake device for a gas turbine includes an air intake assembly.

[0041] The intake system includes a load section for absorbing air and a power section for generating electricity; the load section is used for absorbing air and generating electricity; the power section is used for outputting power.

[0042] The load section and power section have separate air intakes; the air intake adopts a push-pull flow control structure.

[0043] When the aircraft does not require bleed air or power generation, the load section stops working and closes the load section air intake passage by adjusting the flow control structure.

[0044] In this embodiment, the push-pull flow control structure is a fence type or a grid type.

[0045] In this embodiment, the fence or mesh of the load section is fixed, and the fence channel or grid channel of the power section is intersected with the load section.

[0046] In this embodiment, the power section fence or grid corresponding to the load section fence channel or grid channel is provided with two layers, wherein the upper layer can slide left and right, and ball bearings or rollers are provided between the two layers of fence or grid.

[0047] In practice, ball bearings or rollers are installed between the two layers of fences or grilles to reduce sliding resistance, facilitate sliding between the upper and lower layers, and make air intake control more convenient and accurate.

[0048] To enable those skilled in the art to better understand this disclosure, the principles of this disclosure are explained below in conjunction with the accompanying drawings:

[0049] This disclosure relates to an auxiliary power unit with dual-sided object air intake under load, wherein the load section and the power section have separate air intakes, such as... Figure 1 The air intake can be either a grille type or a grid type. Figure 2 and Figure 3 The load section's fence or mesh is fixed, while the power section's fence or grid channel intersects with the load section. The power section's fence or grid, corresponding to the load section's fence or grid channel, has two layers, with the outer layer sliding left and right. To facilitate sliding, ball bearings or rollers can be installed between the two layers of fence or grid. Figure 2 This is a schematic diagram of a fence, where left: the passage is fully open, middle: the passage is half open, and right: the passage is fully closed; Figure 3 This is a schematic diagram of a grid system, where left: channel fully open, middle: channel half open, and right: channel fully closed; Figure 4 This is a schematic diagram of a fully open fence-style structure. Figure 5 This is a schematic diagram of a fence-style semi-open structure. Figure 6 This is a schematic diagram of a fully enclosed fence-type structure. Figure 7 This is a schematic diagram of a fully open grille design. Figure 8 This is a schematic diagram of a grid-type semi-open structure. Figure 9 This is a schematic diagram of a fully closed grille-type grille.

[0050] After the grid is added, the airflow parameters are not non-uniform along the circumferential direction and there is no circumferential gradient, so no circumferential excitation source will be generated.

[0051] Although the present disclosure has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features; and these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present disclosure.

Claims

1. An air intake device for a gas turbine, characterized in that, The intake system includes a load section for absorbing air and a power section for generating electricity; the load section is used for absorbing air and generating electricity; the power section is used for outputting power. The load section and power section have separate air intakes; the air intake adopts a push-pull flow control structure. When no bleed air or power generation is required, the load section stops working and the load section air intake passage is closed by adjusting the flow control structure; The push-pull flow control structure includes a fence or grille; The fences of the load section are fixed, while the fences of the power section are set at intervals and cross each other with the fences of the load section. The power section fence has two layers; The upper layer of the power section fence can slide left and right, and there are ball bearings or rollers between the two layers of fence; The grid of the load section is fixed, and the grid of the power section is set at intervals and crosses with that of the load section; The power section grille has two layers; The upper layer of the power section grille can slide left and right, and there are ball bearings or rollers between the two layers of grille.

2. The gas turbine intake device according to claim 1, characterized in that, The power section fence has at least two layers.

3. The gas turbine intake device according to claim 1, characterized in that, The flow control structure is controlled hydraulically.

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