Main mounting section for helicopters and their turboshaft engines

Abstract

The present invention discloses a main mounting section for a helicopter and a turboshaft engine thereof, wherein the main mounting section for the turboshaft engine comprises a coaxially nested mounting tube, a flow channel tube and a lining tube, the flow channel tube is sleeved on the outer periphery of the mounting tube and enclosed with the mounting tube to form a cavity, the lining tube sequentially divides the cavity into a first hot gas channel and a second hot gas channel in a radially outward direction, the radial width of the second hot gas channel is smaller than the radial width of the first hot gas channel; the first end of the mounting tube is provided with an air inlet hole for introducing high-temperature gas into the first hot gas channel, the lining tube is provided with an air guide hole for connecting the first hot gas channel and the second hot gas channel at the second end of the mounting tube, and the outer wall of the flow channel tube is provided with an exhaust hole for discharging high-temperature gas in the second hot gas channel at the first end of the mounting tube. The main mounting section for the turboshaft engine provided by the present invention can achieve double-layer hot gas coverage, and utilize the caliber contraction effect to increase the flow rate of the high-temperature gas, thereby achieving a better anti-icing effect.

Description

Technical Field

[0001] The invention relates to the technical field of aviation engine installation, in particular to a main installation node for a turboshaft engine and a helicopter using the main installation node for a turboshaft engine. Background Art

[0002] The aviation turboshaft engine needs to be installed in the helicopter cabin through the main installation node, and the turboshaft engine needs to be fixed through the main installation node, and the power transmission between the turboshaft engine and the helicopter platform is realized at the same time. The existing main installation node is usually installed axially in front and behind, and the intermediate force transmission structure adopts a simple straight cylinder structure with a single function. However, since the structural layout and aerodynamic performance need to be comprehensively considered when designing a turboshaft engine, the main installation outer surface is usually used as part of the inlet flow channel. At the same time, in order to ensure better intake performance, the inlet flow channel surface sometimes needs to be designed as a curved surface. At this time, in order to ensure the safe use of the turboshaft engine under icing conditions, the curved flow channel surface needs to be designed for anti-icing, but the existing simple straight cylinder structure of the main installation node cannot meet the anti-icing design requirements of such turboshaft engines. Summary of the invention

[0003] The present invention primarily provides a main mounting section for a turboshaft engine, so as to solve the technical problem that the main mounting section of the existing turboshaft engine does not have an air intake anti-icing function.

[0004] The present invention also provides a helicopter, which adopts the main mounting section for the turboshaft engine.

[0005] According to one aspect of the present invention, there is provided a main mounting section for a turboshaft engine, comprising a coaxially nested mounting tube, a flow channel tube and a liner tube, wherein a first end of the mounting tube is used to connect to the turboshaft engine, and a second end of the mounting tube is used to connect to a transmission sleeve of a helicopter, the flow channel tube is sleeved on the outer circumference of the mounting tube and enclosed with the mounting tube to form a cavity, the liner tube is arranged in the cavity and divides the cavity into a first hot gas channel and a second hot gas channel in sequence along a radially outward direction, wherein the radial width of the second hot gas channel is smaller than the radial width of the first hot gas channel;

[0006] The first end of the mounting tube is provided with an air inlet hole for introducing high-temperature gas into the first hot gas channel, the second end of the mounting tube is provided with an air guide hole for connecting the first hot gas channel and the second hot gas channel, and the outer wall of the flow channel tube is provided with an exhaust hole for discharging high-temperature gas in the second hot gas channel at the first end of the mounting tube.

[0007] Preferably, the flow channel tube is configured as an arc surface structure that expands radially outward along the direction from the second end to the first end of the mounting tube, thereby forming an intake flow channel of the turboshaft engine on the outer wall of the flow channel tube and gradually reducing the radial width of the cavity along the direction from the first end to the second end of the mounting tube.

[0008] Preferably, the liner tube includes a guide ring and an air induction ring, the second hot gas channel is formed by the gap between the guide ring and the runner tube, and the guide ring is adapted to the arc surface structure of the runner tube, so that the radial width of the second hot gas channel at different axial positions is maintained within a preset range;

[0009] The air bleed ring is arranged on one end of the guide ring facing the second end of the mounting tube, the first end of the air bleed ring is connected to the guide ring, the second end of the air bleed ring is connected to the second end of the mounting tube after being bent radially inward, the air bleed ring is used to enclose with the flow channel tube to form an air bleed cavity connected to the second hot gas channel, the air guide hole is opened on the air bleed ring and is used to introduce the high-temperature gas in the first hot gas channel into the air bleed cavity, and the radial width of the air bleed cavity is greater than the radial width of the second hot gas channel.

[0010] Preferably, a plurality of positioning protrusions are arranged on a side of the guide ring facing the flow channel tube, and the positioning protrusions are used to abut against the flow channel tube and position the distance between the guide ring and the flow channel tube.

[0011] Preferably, the first end of the mounting tube is provided with a support edge extending radially outward, the air inlet is opened on the support edge, one end of the guide ring facing the first end of the mounting tube is connected to the support edge, and one end of the flow channel tube facing the first end of the mounting tube is supported by the support edge and extends axially to form an extension portion beyond the guide ring;

[0012] The main mounting node for the turboshaft engine also includes a sealing ring, a first end of which is connected to the supporting edge, and a second end of which is connected to the extension portion and is used to seal the end of the second hot gas channel.

[0013] Preferably, the main mounting section for the turboshaft engine further comprises an oil drain pipe, a first end of which is connected to the bottom of the mounting tube, and a second end of which is connected to an oil drain hole preset on the supporting edge.

[0014] Preferably, the air guide holes are configured as circular holes, and a plurality of the air guide holes are equidistantly arranged along the circumference of the lining tube.

[0015] Preferably, the exhaust hole is configured as a strip hole extending along the circumference of the flow channel cylinder, and a plurality of the exhaust holes are equidistantly arranged along the circumference of the flow channel cylinder.

[0016] Preferably, a first mounting edge is provided on the inner wall of the first end of the mounting tube, and a second mounting edge is provided on the inner wall of the second end of the mounting tube, the first mounting edge is used to connect to the turboshaft engine, and the second mounting edge is used to connect to the transmission shaft sleeve of the helicopter.

[0017] As a second aspect, the present invention also provides a helicopter, comprising a turboshaft engine and a transmission sleeve, and a main mounting section for the turboshaft engine, wherein the first end of the mounting tube is connected to the turboshaft engine, and the second end of the mounting tube is connected to the transmission sleeve.

[0018] The present invention has the following beneficial effects:

[0019] In the main mounting section for the turboshaft engine provided by the present invention, a cavity is formed by enclosing the flow channel tube and the mounting tube, and the cavity is divided into a first hot gas channel and a second hot gas channel in sequence along the radial outward direction by the lining tube. After the high-temperature gas flows along the first hot gas channel from the first end to the second end of the mounting tube, it can enter the second hot gas channel and flow along the second hot gas channel from the second end to the first end of the mounting tube, thereby realizing double-layer hot gas coverage, efficiently utilizing the high-temperature gas for reciprocating heating, and effectively improving the heating and anti-icing effect. More importantly, since the radial width of the second hot gas channel is smaller than the radial width of the first hot gas channel, after the high-temperature gas enters the second hot gas channel from the first hot gas channel, the effect of the contraction of the interlayer space diameter can be utilized to increase the flow velocity of the high-temperature gas, thereby enabling the high-temperature gas to more efficiently heat and anti-ic the outer wall of the flow channel tube when passing through the second hot gas channel.

[0020] In addition to the above-described purposes, features and advantages, the present invention has other purposes, features and advantages. The present invention will be further described in detail with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] The drawings constituting a part of this application are used to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation of the present invention. In the drawings:

[0022] Figure 1 A three-dimensional view of a main mounting section for a turboshaft engine provided by an embodiment of the present invention;

[0023] Figure 2 for Figure 1 A cross-sectional structural diagram of a main mounting section for a turboshaft engine shown;

[0024] Figure 3 for Figure 2 A schematic diagram of the structure of a liner barrel in a main mounting section for a turboshaft engine is shown.

[0025] Legend:

[0026] 1000. Main mounting section for turboshaft engine; 1. Mounting tube; 11. Support edge; 111. Air inlet; 112. Oil drain hole; 12. First mounting edge; 13. Second mounting edge; 2. Flow channel tube; 21. Exhaust hole; 22. Extension; 3. Lining tube; 31. Guide ring; 311. Positioning protrusion; 32. Air bleed ring; 321. Air guide hole; 4. Sealing ring; 5. Oil drain pipe; 100. First hot gas channel; 200. Second hot gas channel; 300. Air bleed cavity. DETAILED DESCRIPTION

[0027] The embodiments of the present invention are described in detail below with reference to the accompanying drawings. However, the present invention can be implemented in many different ways as defined and covered below.

[0028] Figures 1 to 3 Together, a main mounting section for a turboshaft engine provided by an embodiment of the present invention is shown, which is used to install the turboshaft engine and realize power transmission between the turboshaft engine and the helicopter platform. The outer peripheral wall can be efficiently heated and de-iced, so that the outer peripheral wall can be used as an inlet airflow duct while ensuring the safe use of the turboshaft engine under low temperature conditions.

[0029] Please combine Figure 1 and Figure 2 The main installation section 1000 for the turboshaft engine comprises a coaxially nested installation tube 1, a flow channel tube 2 and a liner tube 3. The first end of the installation tube 1 is used to connect with the turboshaft engine, and the second end of the installation tube 1 is used to connect with the transmission sleeve of the helicopter. The flow channel tube 2 is sleeved on the outer periphery of the installation tube 1 and enclosed with the installation tube 1 to form a cavity. The outer wall of the flow channel tube 2 is used as the inlet flow channel of the turboshaft engine. The liner tube 3 is arranged in the cavity and divides the cavity into a first hot gas channel 100 and a second hot gas channel 200 in the radial outward direction, that is, the first hot gas channel 100 is arranged on the radial inner side of the cavity (the side close to the installation tube 1), and the second hot gas channel 200 is arranged on the radial outer side of the cavity (the side close to the flow channel tube 2). The radial width of the second hot gas channel 200 is smaller than the radial width of the first hot gas channel 100.

[0030] Furthermore, an air inlet hole 111 for introducing high-temperature gas into the first hot gas channel 100 is provided at the first end of the mounting tube 1, an air guide hole 321 for connecting the first hot gas channel 100 and the second hot gas channel 200 is opened at the second end of the mounting tube 1, and an exhaust hole 21 for discharging the high-temperature gas in the second hot gas channel 200 is opened on the outer wall of the flow channel tube 2 at the first end of the mounting tube 1.

[0031] In the main installation section 1000 for the turboshaft engine, a cavity is formed by enclosing the flow channel tube 2 and the installation tube 1, and the cavity is sequentially divided into a first hot gas channel 100 and a second hot gas channel 200 in the radial outward direction by the lining tube 3. After the high-temperature gas flows from the first end of the installation tube 1 to the second end along the first hot gas channel 100, it can enter the second hot gas channel 200 and flow from the second end of the installation tube 1 to the first end along the second hot gas channel 200, so as to achieve double-layer hot gas coverage, efficiently utilize high-temperature gas for reciprocating heating, and effectively improve the heating and anti-icing effect. More importantly, since the radial width of the second hot gas channel 200 is smaller than the radial width of the first hot gas channel 100, after the high-temperature gas enters the second hot gas channel 200 from the first hot gas channel 100, the flow velocity of the high-temperature gas can be increased by utilizing the effect of the shrinkage of the interlayer space caliber, so that the high-temperature gas can more efficiently heat and anti-ic the outer wall of the flow channel tube 2 when passing through the second hot gas channel 200.

[0032] like Figure 2 As shown, the flow channel tube 2 is configured as a curved surface structure that expands radially outward along the direction from the second end to the first end of the mounting tube 1, thereby forming an intake flow channel of the turboshaft engine on the outer wall of the flow channel tube 2, and the radial width of the cavity is gradually reduced along the direction from the first end to the second end of the mounting tube 1, so that the radial width of the first hot gas channel 100 is gradually reduced along the direction from the first end to the second end of the mounting tube 1, thereby gradually increasing the flow velocity of the high-temperature gas when flowing along the first hot gas channel 100, and utilizing the curved surface structure of the flow channel tube 2 itself to increase the flow velocity of the high-temperature gas, thereby further enhancing the heating effect.

[0033] Please combine Figure 2 and Figure 3, the liner tube 3 includes a guide ring 31 and an air induction ring 32, the second hot gas channel 200 is formed by the gap between the guide ring 31 and the runner tube 2, and the guide ring 31 is adapted to the arc surface structure of the runner tube 2, so that the radial width of the second hot gas channel 100 at different axial positions is maintained within a preset range. Specifically, the guide ring 31 is set to an arc shape that is adapted to the arc surface structure of the runner tube 2 along the axial direction, so that the guide ring 31 can be set closely to the runner tube 2 along the entire axial direction, so that the radial width of the second hot gas channel 100 at different axial positions is maintained within a preset range, and the preset range can be adjusted according to the actual size of the main mounting section 1000 for the turboshaft engine and the anti-icing requirements, and the specific value can be 1-10mm.

[0034] Furthermore, the air inlet ring 32 is arranged on one end of the guide ring 31 facing the second end of the mounting tube 1, the first end of the air inlet ring 32 is connected to the guide ring 31, and the second end of the air inlet ring 32 is connected to the second end of the mounting tube 1 after being bent radially inward, the air inlet ring 32 is used to enclose with the flow channel tube 2 to form an air inlet cavity 300 connected to the second hot gas channel 200, the air guide hole 321 is opened on the air inlet ring 32 and is used to introduce the high-temperature gas in the first hot gas channel 100 into the air inlet cavity 300, and the radial width of the air inlet cavity 300 is greater than the radial width of the second hot gas channel 200. Since the airflow directions of the first hot gas channel 100 and the second hot gas channel 200 are opposite, the high-temperature gas needs to reverse flow quickly. At this time, the high-temperature gas in the first hot gas channel 100 is first introduced through the larger-diameter air inlet cavity 300, so that the high-temperature gas can smoothly reverse in the air inlet cavity 300 and then accelerate along the smaller-diameter second hot gas channel 200 to ensure smooth airflow and avoid blockage.

[0035] Preferably, a plurality of positioning protrusions 311 are arranged on the side of the guide ring 31 facing the runner tube 2, and the plurality of positioning protrusions 311 are arranged along the circumference of the guide ring 31, and the positioning protrusions 311 are used to abut against the inner wall of the runner tube 2, so that the distance between the guide ring 31 and the runner tube 2 can be positioned by the positioning protrusions 311, and the distance between the guide ring 31 and the runner tube 2 at different positions can be controlled at the same time. The positioning structure is simple and efficient, ensuring that the second hot gas channel 200 between the guide ring 31 and the runner tube 2 is unobstructed, and avoiding that the guide ring 31 is close to the runner tube 2 and causes the channel to be blocked.

[0036] like Figure 2As shown, the first end of the mounting tube 1 is provided with a support edge 11 extending radially outward, the air inlet is opened on the support edge 11 along the axial direction 111 of the mounting tube 1, the end of the guide ring 31 facing the first end of the mounting tube 1 is connected to the support edge 11, and the end of the flow channel tube 2 facing the first end of the mounting tube 1 is supported by the support edge 11 and extends axially to form an extension portion 22 that exceeds the guide ring 31. Specifically, taking the direction shown in the figure as an example for explanation, the right end of the guide ring 31 is connected to the support edge 11, the right end of the flow channel tube 2 is supported by the support edge 11 and extends axially to form an extension portion 22 that exceeds the right end of the guide ring 31.

[0037] Furthermore, the main mounting node 1000 for the turboshaft engine further includes a sealing ring 4, a first end of which is connected to the supporting edge 11, and a second end of which is connected to the extending portion 22 and is used to seal the end of the second hot gas passage 200. The end of the second hot gas passage 200 is sealed by the sealing ring 4, so that the high-temperature gas in the second hot gas passage 200 is discharged along the exhaust hole 21 after fully flowing through the inner wall of the flow channel tube 2, thereby avoiding gas leakage.

[0038] Preferably, the main mounting section 1000 for the turboshaft engine further comprises an oil drain pipe 5, the first end of which is connected to the bottom of the mounting tube 1, and the second end of which is connected to the preset oil drain hole 112 on the supporting edge 11. Since the power turbine output unit of the turboshaft engine passes through the interior of the mounting tube 1 when in use, some leaked lubricating oil may accumulate in the inner cavity of the mounting tube 1. By opening a hole at the bottom of the mounting tube 1 to provide the oil drain pipe 5 to guide the lubricating oil in the inner cavity of the mounting tube 1, the lubricating oil accumulation drain function can be realized, ensuring the sufficient draining of the residual oil in the mounting tube 1, and preventing the excessive accumulation of residual oil from leaking into the flow channel of the turboshaft engine.

[0039] like Figure 3 As shown, the air guide hole 321 is set as a circular hole, and a plurality of the air guide holes 321 are arranged equidistantly along the circumference of the liner tube 3. The air guide hole 321 is a circular hole, which can reduce the disturbance of the air flow through its smooth edge, has less resistance to the air flow, can guide the high-temperature air flow to pass smoothly and quickly, and improve the flow rate.

[0040] like Figure 1 As shown, the exhaust hole 21 is configured as a strip hole extending along the circumference of the flow channel tube 2, and a plurality of the exhaust holes 21 are arranged equidistantly along the circumference of the flow channel tube 2. The exhaust hole 21 is a strip hole, which can have a larger ventilation volume, can be better aligned with the airflow direction, and improve the exhaust effect.

[0041] like Figure 2 As shown, a first mounting edge 12 is provided on the inner wall of the first end of the mounting tube 1, and a second mounting edge 13 is provided on the inner wall of the second end of the mounting tube 1. The first mounting edge 12 is used to connect with the turboshaft engine, and the second mounting edge 13 is used to connect with the transmission shaft sleeve of the helicopter for quick installation and positioning.

[0042] As a second aspect, the present invention further provides a helicopter (not shown in the figure, the same below), comprising a turboshaft engine and a transmission sleeve, and a main mounting section 1000 for the turboshaft engine, wherein the first end of the mounting tube 1 is connected to the turboshaft engine, and the second end of the mounting tube 1 is connected to the transmission sleeve. The turboshaft engine is installed and powered by the main mounting section 1000, which can be used as an inlet flow passage for the turboshaft engine, has better anti-icing and lubricating oil accumulation drainage functions, and effectively improves the safety and applicability of the helicopter.

[0043] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A main mounting section for a turboshaft engine, characterized in that: The invention comprises a coaxially nested mounting tube (1), a flow channel tube (2) and a liner tube (3), wherein a first end of the mounting tube (1) is used to be connected to a turboshaft engine, and a second end of the mounting tube (1) is used to be connected to a transmission sleeve of a helicopter, the flow channel tube (2) is sleeved on the outer circumference of the mounting tube (1) and enclosed with the mounting tube (1) to form a cavity, the liner tube (3) is arranged in the cavity and divides the cavity into a first hot gas channel (100) and a second hot gas channel (200) in sequence in a radially outward direction, and the radial width of the second hot gas channel (200) is smaller than the radial width of the first hot gas channel (100); The first end of the mounting tube (1) is provided with an air inlet (111) for introducing high-temperature gas into the first hot gas channel (100); the lining tube (3) is provided with an air guide hole (321) for connecting the first hot gas channel (100) and the second hot gas channel (200) at the second end of the mounting tube (1); and the outer wall of the flow channel tube (2) is provided with an exhaust hole (21) for exhausting high-temperature gas in the second hot gas channel (200) at the first end of the mounting tube (1); The flow channel tube (2) is configured as a curved surface structure that expands radially outward in the direction from the second end to the first end of the mounting tube (1), thereby forming an inlet flow channel of the turboshaft engine on the outer wall of the flow channel tube (2) and gradually reducing the radial width of the cavity in the direction from the first end to the second end of the mounting tube (1).

2. The main mounting section for a turboshaft engine according to claim 1, characterized in that: The liner tube (3) comprises a guide ring (31) and an air induction ring (32); the second hot gas channel (200) is formed by a gap between the guide ring (31) and the flow channel tube (2); the guide ring (31) is adapted to the arc surface structure of the flow channel tube (2) so that the radial width of the second hot gas channel (200) at different axial positions is maintained within a preset range; The air entraining ring (32) is arranged on an end of the guide ring (31) facing the second end of the mounting tube (1); the first end of the air entraining ring (32) is connected to the guide ring (31); the second end of the air entraining ring (32) is connected to the second end of the mounting tube (1) after being bent radially inward; the air entraining ring (32) is used to enclose with the flow channel tube (2) to form an air entraining cavity (300) communicating with the second hot gas channel (200); the air guide hole (321) is provided on the air entraining ring (32) and is used to guide the high-temperature gas in the first hot gas channel (100) into the air entraining cavity (300); the radial width of the air entraining cavity (300) is greater than the radial width of the second hot gas channel (200).

3. The main mounting section for a turboshaft engine according to claim 2, characterized in that: A plurality of positioning protrusions (311) are arranged on a surface of the guide ring (31) facing the flow channel tube (2), and the positioning protrusions (311) are used to abut against the flow channel tube (2) and to position the distance between the guide ring (31) and the flow channel tube (2).

4. The main mounting section for a turboshaft engine according to claim 2, characterized in that: The first end of the mounting tube (1) is provided with a support edge (11) extending radially outward, the air inlet hole (111) is formed on the support edge (11), an end of the guide ring (31) facing the first end of the mounting tube (1) is connected to the support edge (11), and an end of the flow channel tube (2) facing the first end of the mounting tube (1) is supported by the support edge (11) and extends axially to form an extension portion (22) extending beyond the guide ring (31); The main mounting node for the turboshaft engine further comprises a sealing ring (4), a first end of the sealing ring (4) being connected to the supporting edge (11), and a second end of the sealing ring (4) being connected to the extension portion (22) and used for sealing the end of the second hot gas channel (200).

5. The main mounting section for a turboshaft engine according to claim 4, characterized in that: The main installation section for the turboshaft engine further comprises an oil drain pipe (5), a first end of the oil drain pipe (5) being connected to the bottom of the installation cylinder (1), and a second end of the oil drain pipe (5) being connected to an oil drain hole (112) preset on the supporting edge (11).

6. The main mounting section for a turboshaft engine according to claim 1, characterized in that: The air guide holes (321) are configured as circular holes, and a plurality of the air guide holes (321) are arranged equidistantly along the circumference of the liner tube (3).

7. The main mounting section for a turboshaft engine according to claim 1, characterized in that: The exhaust hole (21) is provided as a strip-shaped hole extending along the circumference of the flow channel cylinder (2), and a plurality of the exhaust holes (21) are arranged at equal intervals along the circumference of the flow channel cylinder (2).

8. The main mounting section for a turboshaft engine according to claim 1, characterized in that: A first mounting edge (12) is provided on the inner wall of the first end of the mounting tube (1), and a second mounting edge (13) is provided on the inner wall of the second end of the mounting tube (1); the first mounting edge (12) is used to connect to a turboshaft engine, and the second mounting edge (13) is used to connect to a transmission shaft sleeve of a helicopter.

9. A helicopter, comprising a turboshaft engine and a transmission sleeve, characterized in that: The helicopter further comprises a main mounting section for a turboshaft engine as claimed in any one of claims 1 to 8, wherein a first end of the mounting tube (1) is connected to the turboshaft engine, and a second end of the mounting tube (1) is connected to the transmission sleeve.

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