Porous combined jet based turbine guide vane flow regulation structure and method

Abstract

The present application relates to the technical field of aero-engine, and discloses a turbine guide vane flow regulating structure and method based on a porous combined jet, wherein a first jet component and a second jet component are respectively arranged on the corresponding guide vane back of the turbine guide vane cascade channel in the upstream and downstream directions of the flow direction, when the first jet component sprays the airflow in the upstream direction of the flow direction, due to the penetration of the airflow to the main flow, a backflow area is formed downstream of the first jet component, the low-speed fluid in the backflow area blocks the main flow channel of the turbine guide vane, reduces the aerodynamic throat area, and achieves the throttling effect, when the second jet component sprays the airflow in the downstream direction of the flow direction, the airflow can be supplemented to the main flow, further increasing the outlet flow of the high-pressure turbine guide vane, thereby widening the regulating range of the same cold gas flow to the high-pressure turbine outlet flow, and being beneficial to improving the turbine aerodynamic and cooling efficiency.

Description

Technical Field

[0001] This invention relates to the field of aero-engine technology, and discloses a turbine guide flow regulation structure and method based on a multi-hole combined jet. Background Technology

[0002] Traditional aero-engines typically focus on a specific operating condition while simultaneously considering performance under other conditions. However, with technological advancements, existing aero-engines are increasingly unable to meet the higher performance requirements of aircraft. To address the need for wider flight envelopes and reduced fuel consumption under varying flight conditions in advanced aircraft, the concept of variable cycle aero-engines has been proposed. Its main characteristic is maintaining low fuel consumption under different thrust conditions through bypass ratio adjustment. Specifically, this is achieved by adjusting the turbine guide vane flow rate under different operating conditions, altering the compression system speed matching, and simultaneously using a duct ejector to actively control the flow characteristics of the fan's outer bypass duct, thereby changing the engine's bypass ratio by varying the flow rates of the inner and outer bypass ducts. This alters the engine's thermodynamic cycle, hence the name variable cycle engine. Typical examples include GEAE's XA100 and PW's XA101, which employ adjustable flow rates from a rotary low-pressure turbine.

[0003] Turbine guide vane flow regulation is one of the important technical means to achieve variable cycle aero-engines. Adjustable high-pressure turbine flow can increase the core engine pressure ratio in the bypass ratio increase mode, solving the problem of core engine pressure ratio decrease when the bypass ratio increases under low-pressure turbine adjustment, and further reducing the overall fuel consumption rate at critical operating points. Therefore, for variable cycle aero-engines, adjustable high-pressure turbine flow has better effects than adjustable low-pressure turbine flow.

[0004] Existing high-pressure turbine guide vane flow regulation methods adjust the flow area of ​​the high-pressure turbine guide vanes mechanically, thereby regulating the turbine flow. This method suffers from several common drawbacks and difficulties. First, the mechanical adjustment mechanism is structurally difficult to design, and its introduction inevitably increases the turbine's weight significantly, hindering weight reduction designs for aero-engines. Second, high-pressure turbines operate in high-temperature, high-pressure environments, making lubrication of the adjustment mechanism challenging. Furthermore, the extremely high temperature gradient causes uneven expansion of different parts of the adjustment mechanism, potentially leading to failure due to thermal stress. Additionally, high-pressure turbine performance is extremely sensitive to minute geometric changes; the low adjustment precision of mechanical structures makes it difficult to meet the requirements of small-angle, high-precision adjustments, and the resulting adjustment errors significantly impact turbine performance. Finally, the additional mechanical adjustment mechanism increases the turbine's complexity, hindering improvements in high-pressure turbine reliability. Summary of the Invention

[0005] The purpose of this invention is to provide a turbine guide flow regulation structure and method based on a multi-hole combined jet, which can broaden the regulation range of the high-pressure turbine outlet flow for the same cold air flow, and is beneficial to improving turbine aerodynamic and cooling efficiency.

[0006] To achieve the above-mentioned technical effects, the technical solution adopted by the present invention is as follows:

[0007] The turbine guide vane flow regulation structure based on porous combined jet includes:

[0008] The first jet assembly is disposed on the back of the guide blade corresponding to the turbine guide vane passage, and is used to jet air upstream in the direction of airflow within the vane passage.

[0009] The second jet assembly is disposed on the back of the guide blade corresponding to the turbine guide vane passage, and is used to jet air downstream in the direction of airflow within the vane passage.

[0010] An air supply assembly is used to provide jet airflow to the first jet assembly and the second jet assembly, respectively.

[0011] Furthermore, both the first jet assembly and the second jet assembly are jet holes, and the first jet assembly and the second jet assembly share the same jet outlet on the back of the corresponding guide vane, forming a V-shaped structure.

[0012] Furthermore, the jet outlet is located on the back of the guide blade corresponding to the throat position of the turbine guide vane passage.

[0013] Furthermore, an on / off valve is provided on the jet outlet, which is used to close the jet path of the second jet assembly when the first jet assembly is working, or to close the jet path of the first jet assembly when the second jet assembly is working.

[0014] Furthermore, the central axis of the first jet assembly intersects the central axis of the second jet assembly at the center point of the jet outlet; the opening and closing valve is a plate-shaped structure, and the opening and closing valve is hinged between the outlet end of the first jet assembly and the outlet end of the second jet assembly through a hinge point.

[0015] Furthermore, the jet outlet angle of the first jet assembly ranges from 30 degrees to 60 degrees; the jet outlet angle of the first jet assembly is the angle between the jet airflow ejected by the first jet assembly and the jet outlet normal, and the direction is tilted towards the upstream of the turbine guide vane passage.

[0016] Furthermore, the jet outlet angle of the second jet assembly ranges from 45 degrees to 60 degrees; the jet outlet angle of the second jet assembly is the angle between the jet airflow ejected by the second jet assembly and the jet outlet normal, and the direction is tilted towards the downstream of the turbine guide vane passage.

[0017] To achieve the above-mentioned technical effects, the present invention also provides a method for regulating the flow rate of a turbine guide vane based on a multi-hole combined jet. This method, based on the aforementioned turbine guide vane flow rate regulation structure, includes:

[0018] Determine the outlet flow control requirements of the turbine guide vane passage, which include reducing or increasing the outlet flow.

[0019] According to the determined turbine guide vane flow control requirements, airflow is injected into the turbine guide vane passage using a first jet assembly or a second jet assembly; wherein, when the control requirement is to reduce the outlet flow, airflow is injected into the turbine guide vane passage using the first jet assembly at a first preset jet flow; when the control requirement is to increase the outlet flow, airflow is injected into the turbine guide vane passage using the second jet assembly at a second preset jet flow.

[0020] Furthermore, the first preset jet flow rate ,in The design flow rate of the turbine guide vane passage without the first jet assembly and the second jet assembly. The throttling efficiency of the turbine guide vane passage. To control the target outlet flow rate of the turbine guide vane passage when the demand is reduced to decrease the outlet flow rate; a second preset jet flow rate. ,in To control the target outlet flow rate of the turbine guide vane passage when the demand increases the outlet flow rate.

[0021] Compared with the prior art, the beneficial effects of this invention are:

[0022] 1. This invention involves assembling a first jet assembly and a second jet assembly on the back of the guide blades corresponding to the turbine guide vane passage, respectively, upstream and downstream of the incoming flow direction. When the first jet assembly ejects airflow upstream of the incoming flow direction, a recirculation zone is formed downstream of the first jet assembly due to the penetrating effect of the airflow on the mainstream incoming flow. The low-speed fluid in the recirculation zone blocks the mainstream flow channel of the turbine guide vane, reducing the aerodynamic throat area and achieving a throttling effect. When the second jet assembly ejects airflow downstream of the incoming flow direction, this portion of the airflow can replenish the mainstream, further increasing the outlet flow rate of the high-pressure turbine guide vane.

[0023] 2. This invention can make fuller use of the cold air flow by controlling the jet's injection direction, thus widening the adjustment range of the high-pressure turbine outlet flow for the same cold air flow. Furthermore, adjusting the high-pressure turbine guide flow using the cold air jet does not involve complex mechanical adjustment mechanisms, which helps reduce the overall weight of the turbine and improve the reliability of the adjustment system in high-temperature and high-pressure environments. In addition, the aerodynamic adjustment method can be combined with the integrated design of the cold channel inside the guide, without introducing additional adjustable clearance, which helps improve the turbine's aerodynamic and cooling efficiency. Attached Figure Description

[0024] Figure 1 The embodiment shows a turbine guide flow regulation structure based on a multi-hole combined jet.

[0025] Figure 2 A schematic diagram of a V-shaped structure formed by the first jet assembly and the second jet assembly;

[0026] Figure 3 for Figure 2 A magnified schematic diagram of part A in the middle;

[0027] Figure 4 This is a schematic diagram of the structure when the on / off valve is switched to close the outlet end of the first jet component;

[0028] Among them, 1. First jet assembly; 2. Turbine guide vane passage; 3. Guide vane; 4. Second jet assembly; 5. Opening and closing valve. Detailed Implementation

[0029] The present invention will now be described in further detail with reference to the embodiments and accompanying drawings. However, this should not be construed as limiting the scope of the above-described subject matter of the present invention to the following embodiments; all technologies implemented based on the content of the present invention fall within the scope of the present invention.

[0030] Example

[0031] See Figure 1 or Figure 2 A turbine guide flow regulation structure based on a multi-hole combined jet includes:

[0032] The first jet assembly 1 is disposed on the back of the guide blade 3 corresponding to the turbine guide vane passage 2, and is used to jet air upstream in the direction of the airflow in the vane passage.

[0033] The second jet assembly 4 is disposed on the back of the guide blade 3 corresponding to the turbine guide vane passage 2, and is used to jet jets downstream in the direction of airflow within the vane passage.

[0034] An air supply assembly is used to provide jet airflow to the first jet assembly 1 and the second jet assembly 4, respectively.

[0035] In this embodiment, a first jet assembly 1 and a second jet assembly 4 are respectively installed on the back of the guide blades 3 corresponding to the turbine guide vane channel 2, facing upstream and downstream of the incoming flow direction. When the first jet assembly 1 ejects airflow upstream of the incoming flow direction, a backflow zone is formed downstream of the first jet assembly 1 due to the penetration effect of the airflow on the mainstream incoming flow. The low-speed fluid in the backflow zone will block the mainstream flow channel of the turbine guide vane, reducing the aerodynamic throat area and achieving a throttling effect. When the second jet assembly 4 ejects airflow downstream of the incoming flow direction, this part of the airflow can be added to the mainstream, further increasing the outlet flow of the high-pressure turbine guide vane. This embodiment can make fuller use of the cold air flow by controlling the jet injection direction, and widen the adjustment range of the high-pressure turbine outlet flow for the same cold air flow. Moreover, the use of cold air jet to adjust the flow of the high-pressure turbine guide vane does not involve a complex mechanical adjustment mechanism, which is beneficial to reducing the overall weight of the turbine and improving the reliability of the adjustment system in high-temperature and high-pressure environments. In addition, the aerodynamic adjustment method can be combined with the integrated design of the internal cold channel of the guide vane without introducing an additional adjustable clearance, which is beneficial to improving the turbine aerodynamic and cooling efficiency.

[0036] The first jet assembly 1 and the second jet assembly 4 can be separate structures, such as... Figure 1 Each of the shown components has an opening on its corresponding guide vane 3. Alternatively, it can be a single integrated structure. In some other embodiments, the positional relationship between the first jet assembly 1 and the second jet assembly 4 is as follows: Figure 2 As shown, both the first jet assembly 1 and the second jet assembly 4 are jet orifices, and the first jet assembly 1 and the second jet assembly 4 share the same jet outlet on the back of the corresponding guide vane 3, forming a V-shaped structure. By adopting the design of a shared jet outlet, on the one hand, the number of openings on the back of the guide vane 3 can be effectively reduced, mitigating the adverse effects of excessive openings on the structural strength of the blade and improving the reliability and stability of the blade during operation; on the other hand, the shared jet outlet simplifies the structure of the jet assembly, making the layout of the entire jet system more compact, which is conducive to achieving efficient flow regulation within a limited space.

[0037] In this embodiment, the jet outlet is located on the back of the guide blade 3 corresponding to the throat position of the turbine guide vane passage 2. The flow rate through the vane passage is determined by the effective throat area. Setting the jet outlet near the throat allows for more effective interaction with the mainstream airflow, enabling precise intervention of the airflow entering the vane passage, thereby more accurately regulating the outlet flow rate of the turbine guide vane.

[0038] In this embodiment, an on / off valve 5 is provided at the jet outlet. The on / off valve 5 is used to close the jet path of the second jet assembly 4 when the first jet assembly 1 is working, or to close the jet path of the first jet assembly 1 when the second jet assembly 4 is working. The on / off valve 5 can flexibly control the jet channel of another jet assembly that is not working to remain closed according to the actual working state of the first jet assembly 1 and the second jet assembly 4. For example, when the first jet assembly 1 is working, closing the jet path of the second jet assembly 4 can avoid interference from the second jet assembly 4 to the working of the first jet assembly 1, so that the first jet assembly 1 can perform its flow regulation function more stably and efficiently.

[0039] In this embodiment, the central axis of the first jet assembly 1 intersects the central axis of the second jet assembly 4 at the center point of the jet outlet; the on / off valve 5 is a plate-shaped structure, and the on / off valve 5 is hinged between the outlet end of the first jet assembly 1 and the outlet end of the second jet assembly 4 via a hinge point. Figure 3 When the first jet assembly 1 needs to operate, there is no need to manually rotate the on / off valve 5 to the corresponding position. The airflow ejected from the first jet assembly 1 can act on the plate-shaped on / off valve 5, switching the on / off valve 5 to the outlet end of the second jet assembly 4, effectively blocking the airflow through the second jet assembly 4, and ensuring that the airflow ejected from the first jet assembly 1 is not interfered with by the structure of the second jet assembly 4. Figure 4 The second jet component 4 operates in a similar manner to the first jet component 1, and will not be described in detail here. Figure 3 , Figure 4 The arc-shaped dashed line in the figure represents the end movement trajectory of the opening and closing valve 5. When designing the dimensions of the opening and closing valve 5, it is necessary to consider that the opening and closing valve 5 can be matched with the outlet end of the first jet assembly 1 or the outlet end of the second assembly at the corresponding positions.

[0040] In this embodiment, the jet outlet angle of the first jet assembly 1 ranges from 30 degrees to 60 degrees; the jet outlet angle of the first jet assembly 1 is the angle between the jet airflow ejected from the first jet assembly 1 and the jet outlet normal, with the direction tilted towards the upstream of the turbine guide vane passage. This ensures that a sufficiently large backflow zone is generated after the jet is ejected to block the flow channel, thereby reducing the outlet flow of the vane passage and meeting actual processing requirements.

[0041] In this embodiment, the jet outlet angle of the second jet assembly 4 ranges from 45 degrees to 60 degrees; the jet outlet angle of the second jet assembly 4 is the angle between the jet airflow ejected from the second jet assembly 4 and the jet outlet normal, with the direction tilted towards the downstream of the turbine guide vane passage. This ensures that the mixing between this part of the jet and the mainstream is weak, resulting in less aerodynamic loss, while meeting actual processing requirements.

[0042] Based on the same inventive concept, this embodiment also provides a method for regulating the flow rate of a turbine guide vane based on a multi-hole combined jet, including:

[0043] Determine the outlet flow control requirements of the turbine guide vane passage 2, which include reducing or increasing the outlet flow.

[0044] According to the determined turbine guide vane flow control requirements, airflow is injected into the turbine guide vane passage 2 using either the first jet assembly 1 or the second jet assembly 4. When the control requirement is to reduce the outlet flow, airflow is injected into the turbine guide vane passage 2 using the first jet assembly 1 at a first preset jet flow rate. When the control requirement is to increase the outlet flow, airflow is injected into the turbine guide vane passage 2 using the second jet assembly 4 at a second preset jet flow rate.

[0045] In this embodiment, the first preset jet flow rate ,in The design flow rate of the turbine guide vane passage without the first jet assembly and the second jet assembly. The throttling efficiency is related to the outlet jet angle of the first jet assembly and is an inherent property of the throttling device. To control the target outlet flow rate of the turbine guide vane passage when the demand is reduced to decrease the outlet flow rate; a second preset jet flow rate. ,in To control the target outlet flow rate of the turbine guide vane passage when the demand increases the outlet flow rate.

[0046] The above are merely preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A turbine guide flow regulation structure based on a multi-hole combined jet, characterized in that, include: The first jet assembly is disposed on the back of the guide blade corresponding to the turbine guide vane passage, and is used to jet air upstream in the direction of airflow within the vane passage. The second jet assembly is disposed on the back of the guide blade corresponding to the turbine guide vane passage, and is used to jet air downstream in the direction of airflow within the vane passage. An air supply assembly is used to provide jet airflow to the first jet assembly and the second jet assembly, respectively.

2. The turbine guide vane flow regulation structure according to claim 1, characterized in that, Both the first jet assembly and the second jet assembly are jet holes, and the first jet assembly and the second jet assembly share the same jet outlet on the back of the corresponding guide vane, forming a V-shaped structure.

3. The turbine guide vane flow regulation structure according to claim 2, characterized in that, The jet outlet is located on the back of the guide blade corresponding to the throat position of the turbine guide vane passage.

4. The turbine guide vane flow regulation structure according to claim 2, characterized in that, An on / off valve is provided on the jet outlet. The on / off valve is used to close the jet path of the second jet assembly when the first jet assembly is working, or to close the jet path of the first jet assembly when the second jet assembly is working.

5. The turbine guide vane flow regulation structure according to claim 4, characterized in that, The central axis of the first jet assembly intersects the central axis of the second jet assembly at the center point of the jet outlet; the opening and closing valve is a plate-shaped structure, and the opening and closing valve is hinged between the outlet end of the first jet assembly and the outlet end of the second jet assembly through a hinge point.

6. The turbine guide vane flow regulation structure according to claim 2, characterized in that, The jet outlet angle of the first jet assembly ranges from 30 degrees to 60 degrees; the jet outlet angle of the first jet assembly is the angle between the jet airflow ejected by the first jet assembly and the jet outlet normal, and the direction is inclined towards the upstream of the turbine guide vane passage.

7. The turbine guide vane flow regulation structure according to claim 2, characterized in that, The jet outlet angle of the second jet assembly ranges from 45 degrees to 60 degrees; the jet outlet angle of the second jet assembly is the angle between the jet airflow ejected by the second jet assembly and the jet outlet normal, and the direction is inclined towards the downstream of the turbine guide vane passage.

8. A method for regulating the flow rate of a turbine guide vane based on a multi-hole combined jet, the method being based on the turbine guide vane flow rate regulation structure according to any one of claims 1-7, characterized in that, include: Determine the outlet flow control requirements of the turbine guide vane passage, which include reducing or increasing the outlet flow. According to the determined turbine guide vane flow control requirements, airflow is injected into the turbine guide vane passage using a first jet assembly or a second jet assembly; wherein, when the control requirement is to reduce the outlet flow, airflow is injected into the turbine guide vane passage using the first jet assembly at a first preset jet flow; when the control requirement is to increase the outlet flow, airflow is injected into the turbine guide vane passage using the second jet assembly at a second preset jet flow.

9. The turbine guide vane flow regulation method according to claim 8, characterized in that, The first preset jet flow rate ,in The design flow rate of the turbine guide vane passage without the first jet assembly and the second jet assembly. The throttling efficiency of the turbine guide vane passage. To control the target outlet flow rate of the turbine guide vane passage when the demand is reduced; Second preset jet flow rate ,in To control the target outlet flow rate of the turbine guide vane passage when the demand increases the outlet flow rate.

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