Exhaust nozzle structure for gas turbine engine

Abstract

According to one aspect of the present invention, an exhaust nozzle structure of a gas turbine engine is provided, comprising an exhaust nozzle housing portion, a first flap portion, a first slider guide portion, a first slider link portion, a first link member, a first rod portion, a first actuator portion, a second flap portion, a second slider guide portion, a second slider link portion, a second link member, a second rod portion, a second actuator portion, and at least one support portion installed in the exhaust nozzle housing portion, wherein the first rotation axis and the second rotation axis are rotatably installed.

Description

Technology Field

[0001] The present invention relates to an exhaust nozzle structure for a gas turbine engine. Background Technology

[0002] The exhaust nozzle, which discharges exhaust gases from a gas turbine engine, is an important part that can affect engine performance.

[0003] In particular, variable exhaust nozzles can adjust the magnitude of thrust by changing the nozzle area, and furthermore, various exhaust nozzles capable of adjusting the direction of thrust are also being developed.

[0004] Registered Patent Publication No. 10-2182103 discloses a variable exhaust nozzle for a gas turbine engine capable of precisely adjusting the exhaust area. The problem to be solved

[0005] According to one aspect of the present invention, the main objective is to implement an improved exhaust nozzle structure. means of solving the problem

[0006] According to one aspect of the present invention, the exhaust nozzle housing portion; a first flap portion rotatably installed in the exhaust nozzle housing portion; a first slider guide portion installed in the first flap portion; a first slider link portion sliding in the first slider guide portion; a first link member rotatably connected to the first slider link portion and installed to rotate around a first rotation axis; a first rod portion rotatably connected to the first link member; a first actuator portion moving the first rod portion and rotatably connected to the exhaust nozzle housing portion; a second flap portion rotatably installed in the first flap portion; a second slider guide portion installed in the second flap portion; a second slider link portion sliding in the second slider guide portion; a second link member rotatably connected to the second slider link portion and installed to rotate around a second rotation axis; a second rod portion rotatably connected to the second link member; and the exhaust nozzle moving the second rod portion The present invention provides an exhaust nozzle structure for a gas turbine engine comprising: a second actuator portion rotatably connected to a housing portion; and at least one support portion installed in the exhaust nozzle housing portion, wherein the first rotational axis and the second rotational axis are rotatably installed.

[0007] Here, the first slider link portion may include a first air inlet portion for introducing compressed air; and a plurality of first discharge holes formed in a portion facing the first flap portion for discharging the compressed air introduced into the first air inlet portion.

[0008] Here, the second slider link portion may include a second air inlet portion for introducing compressed air; and a plurality of second discharge holes formed in a portion facing the second flap portion for discharging the compressed air introduced into the second air inlet portion. Effects of the invention

[0009] An exhaust nozzle structure of a gas turbine engine according to one aspect of the present invention facilitates the control of the movement of the flap portion by configuring the connection with the flap portion with a slider link portion and a slider guide portion, thereby having the effect of improving the control performance of the exhaust area and thrust direction of the exhaust nozzle structure. Brief explanation of the drawing

[0010] FIG. 1 is a schematic perspective view of an exhaust nozzle structure of a gas turbine engine according to one embodiment of the present invention. Figure 2 is an enlarged perspective view of the upper portion of the exhaust nozzle structure shown in Figure 1. FIG. 3 is a schematic drawing showing a side view of an exhaust nozzle structure of a gas turbine engine according to one embodiment of the present invention. FIG. 4 is a schematic drawing showing a cutaway portion of the first and second slider guide portions and the first and second slider link portions of an exhaust nozzle structure of a gas turbine engine according to one embodiment of the present invention. FIG. 5 is a schematic perspective view illustrating a first link member of an exhaust nozzle structure of a gas turbine engine according to one embodiment of the present invention. FIG. 6 is a schematic perspective view illustrating a second link member of an exhaust nozzle structure of a gas turbine engine according to one embodiment of the present invention. Specific details for implementing the invention

[0011] Hereinafter, the present invention according to a preferred embodiment will be described in detail with reference to the attached drawings. Furthermore, in this specification and drawings, redundant descriptions are omitted for components having substantially the same configuration by using the same reference numerals, and parts in the drawings may be exaggerated in terms of size, length ratio, etc., to aid understanding.

[0012] The present invention will become clear from the embodiments described below in detail together with the accompanying drawings. However, the present invention is not limited to the embodiments disclosed below but may be implemented in various different forms. These embodiments are provided merely to ensure that the disclosure of the present invention is complete and to fully inform those skilled in the art of the scope of the invention, and the present invention is defined only by the scope of the claims.

[0013] Meanwhile, the terms used in this specification are for describing the embodiments and are not intended to limit the invention. In this specification, the singular form includes the plural form unless specifically stated otherwise in the text. As used in this specification, "comprises" and / or "comprising" do not exclude the presence or addition of one or more other components, steps, actions, and / or elements to the mentioned components, steps, actions, and / or elements. Terms such as "first," "second," etc., may be used to describe various components, but the components should not be limited by these terms. The terms are used solely for the purpose of distinguishing one component from another.

[0014] FIG. 1 is a schematic perspective view of an exhaust nozzle structure of a gas turbine engine according to an embodiment of the present invention, and FIG. 2 is an enlarged perspective view of the upper portion of the exhaust nozzle structure shown in FIG. 1. In addition, FIG. 3 is a schematic view showing a side view of an exhaust nozzle structure of a gas turbine engine according to an embodiment of the present invention, and FIG. 4 is a schematic view showing a cutaway portion of the first and second slider guide portions and the first and second slider link portions of an exhaust nozzle structure of a gas turbine engine according to an embodiment of the present invention. In addition, FIG. 5 is a schematic perspective view showing a first link member of an exhaust nozzle structure of a gas turbine engine according to an embodiment of the present invention, and FIG. 6 is a schematic perspective view showing a second link member of an exhaust nozzle structure of a gas turbine engine according to an embodiment of the present invention.

[0015] As illustrated in FIGS. 1 to 6, the exhaust nozzle structure (100) according to the present embodiment includes an exhaust nozzle housing part (110), a first flap part (121), a first slider guide part (122), a first slider link part (123), a first link member (124), a first rod part (125), a first actuator part (126), a second flap part (131), a second slider guide part (132), a second slider link part (133), a second link member (134), a second rod part (135), a second actuator part (136), and a support part (140).

[0016] The exhaust nozzle housing part (110) forms the frame of the exhaust nozzle and can be configured to be connected to the afterburner housing part.

[0017] The exhaust nozzle housing (110) includes an actuator installation part (111), and the actuator installation part (111) supports the first actuator part (126) and the second actuator part (136) so that they can rotate in a hinge structure (H).

[0018] The first flap portion (121) is installed as a pair vertically and is installed so as to be rotatable on the exhaust nozzle housing portion (110) by the first hinge (121a), and the first flap portion (121) performs the function of a convergent flap.

[0019] The first slider guide part (122) is installed on the first flap part (121) and guides the sliding movement of the first slider link part (123).

[0020] As illustrated in FIG. 4, the first slider link portion (123) performs a sliding motion along the lower surface of the rail portion (R) of the first slider guide portion (122). The first slider link portion (123) includes a first link connecting portion (123a), a first link main body portion (123b), a first air inlet portion (123c), and a first discharge hole (123d).

[0021] The first link connection part (123a) is a part connected to the first link member (124) by a hinge structure (H).

[0022] The internal space (C) at the bottom of the first link body part (123b) is empty and functions as an air flow passage.

[0023] The first air inlet (123c) introduces compressed air into the internal space (C). The first air inlet (123c) is connected to a tube (T) that supplies compressed air.

[0024] A plurality of first discharge holes (123d) are formed on the lower surface of the first link body part (123b). That is, the first discharge holes (123d) are formed in the part facing the first flap part (121) and are connected to the internal space (C), so the compressed air in the internal space (C) is discharged through the first discharge holes (123d).

[0025] Due to this configuration of the first slider link section (123), cooling compressed air is introduced into the first air inlet section (123c) through the tube (T), and the cooling compressed air introduced into the first air inlet section (123c) is discharged through the first discharge hole (123d) via the internal space (C). In this way, the lower surface of the first link body section (123b) and the first flap section (121) are cooled by the discharged compressed air, and the friction with the first flap section (121) is reduced during the sliding of the first slider link section (123) by the force exerted by the discharged compressed air. That is, a reaction force is generated by the compressed air discharged through the first discharge hole (123d), so that the gap between the lower surface of the first link body section (123b) and the first flap section (121) is maintained, thereby reducing the frictional force during the sliding movement.

[0026] According to the present embodiment, three first slider guide sections (122) are installed at a predetermined interval on the first flap section (121), and a first slider link section (123) is installed so as to be slidable on each of the installed first slider guide sections (122), but the present invention is not limited thereto. That is, according to the present invention, there is no particular limitation on the number of first slider guide sections (122) installed on the first flap section (121). For example, the number of first slider guide sections (122) installed on the first flap section (121) can be one, two, four, five, etc., and a first slider link section (123) can be installed so as to be slidable on each of the first slider guide sections (122).

[0027] Meanwhile, the first link member (124) is connected to the first slider link member (123) by a hinge structure (H) so as to be rotatable, and is installed to rotate around the first rotation axis (C1).

[0028] As illustrated in FIG. 5, the first link member (124) includes a rod connection part (124a), a slider link connection part (124b), and a first rotation axis (C1).

[0029] The first link member (124) includes one rod connection part (124a) and three slider link connection parts (124b), and the rod connection part (124a) and the slider link connection parts (124b) are connected and fixed to the first rotation axis (C1).

[0030] The first link member (124) according to the present embodiment includes one rod connecting part (124a) and three slider link connecting parts (124b), but the present invention is not limited thereto. That is, there are no special limitations on the configuration of the first link member (124) according to the present invention. For example, the slider link connecting parts (124b) may be configured as one, two, four, five, etc., depending on the number of first slider link parts (123).

[0031] Both ends of the first rotation shaft (C1) are installed to be rotatable on the support member (140). To this end, a shaft-bearing structure may be used at the rotational connection portions of both ends of the first rotation shaft (C1).

[0032] Meanwhile, the first rod portion (125) is rotatably connected to the rod connection portion (124a) of the first link member (124).

[0033] The first actuator part (126) moves the first rod part (125) and is rotatably connected to the exhaust nozzle housing part (110).

[0034] The first actuator part (126) is driven by hydraulic pressure to cause linear motion of the first rod part (125).

[0035] The first actuator unit (126) according to the present embodiment is driven by hydraulic pressure, but the present invention is not limited thereto. That is, there are no special limitations on the driving type of the first actuator unit according to the present invention. For example, the first actuator unit according to the present invention may be composed of pneumatic, linear actuator, electric motor, etc.

[0036] The connecting part (126a) of the first actuator part (126) is connected to the actuator installation part (111) of the exhaust nozzle housing part (110) by a hinge structure (H) so as to be rotatable.

[0037] Meanwhile, the second flap portion (131) is installed as a pair vertically and is installed so as to be rotatable on the first flap portion (121) by a second hinge (131a), and the second flap portion (131) performs the function of a Divergent Flap.

[0038] The second slider guide part (132) is installed on the second flap part (131) and guides the sliding movement of the second slider link part (133).

[0039] As illustrated in FIG. 4, the second slider link portion (133) slides along the lower surface of the rail portion (R) of the second slider guide portion (132). The second slider link portion (133) includes a second link connecting portion (133a), a second link main body portion (133b), a second air inlet portion (133c), and a second discharge hole (133d). Since the configuration of the second slider link portion (133) is substantially the same as the configuration of the first slider link portion (123), the reference numbers of the configurations of the first slider link portion (123) and the second slider link portion (133) are shown together in FIG. 4.

[0040] The second link connection part (133a) is a part connected to the second link member (134) by a hinge structure (H).

[0041] The internal space (C) at the bottom of the second link body (133b) is empty and functions as an air flow passage.

[0042] The second air inlet (133c) introduces compressed air into the internal space (C). The second air inlet (133c) is connected to a tube (T) that supplies compressed air.

[0043] A plurality of second discharge holes (133d) are formed on the lower surface of the second link body part (133b). That is, the second discharge holes (133d) are formed in the part facing the second flap part (131) and are connected to the internal space (C), so the compressed air in the internal space (C) is discharged through the second discharge holes (133d).

[0044] Due to this configuration of the second slider link section (133), cooling compressed air is introduced into the second air inlet section (133c) through the tube (T), and the cooling compressed air introduced into the second air inlet section (133c) is discharged through the second discharge hole (133d) via the internal space (C). In this way, the lower surface of the second link body section (133b) and the second flap section (131) are cooled by the discharged compressed air, and the friction with the second flap section (131) is reduced during the sliding of the second slider link section (133) by the force exerted by the discharged compressed air. That is, a reaction force is generated by the compressed air discharged through the second discharge hole (133d), so that the gap between the lower surface of the second link body section (133b) and the second flap section (131) is maintained, thereby reducing the frictional force during the sliding movement.

[0045] According to the present embodiment, three second slider guide sections (132) are installed at a predetermined interval on the second flap section (131), and a second slider link section (133) is installed so as to be slidable on each of the installed second slider guide sections (132), but the present invention is not limited thereto. That is, according to the present invention, there is no particular limitation on the number of second slider guide sections (132) installed on the second flap section (131). For example, the number of second slider guide sections (132) installed on the second flap section (131) can be one, two, four, five, etc., and a second slider link section (133) can be installed so as to be slidable on each of the second slider guide sections (132).

[0046] Meanwhile, the second link member (134) is connected to the second slider link member (133) by a hinge structure (H) so as to be rotatable, and is installed to rotate around the second rotation axis (C2).

[0047] As shown in FIG. 6, the second link member (134) includes a rod connection part (134a), a slider link connection part (134b), and a second rotation axis (C2).

[0048] The second link member (134) includes one rod connection part (134a) and three slider link connection parts (134b), and the rod connection part (134a) and the slider link connection parts (134b) are connected and fixed to the second rotation axis (C2).

[0049] The second link member (134) according to the present embodiment includes one rod connecting part (134a) and three slider link connecting parts (134b), but the present invention is not limited thereto. That is, there are no special limitations on the configuration of the second link member (134) according to the present invention. For example, the slider link connecting parts (134b) may be configured as one, two, four, five, etc., depending on the number of second slider link parts (133).

[0050] Both ends of the second rotation shaft (C2) are installed to be rotatable on the support member (240). To this end, a shaft-bearing structure may be used at the rotational connection of both ends of the second rotation shaft (C2).

[0051] Meanwhile, the second rod portion (135) is rotatably connected to the rod connection portion (134a) of the second link member (134).

[0052] The second actuator part (136) moves the second rod part (135) and is rotatably connected to the exhaust nozzle housing part (110).

[0053] The second actuator part (136) is driven by hydraulic pressure to cause linear motion of the second rod part (135).

[0054] The second actuator unit (136) according to the present embodiment is driven by hydraulic pressure, but the present invention is not limited thereto. That is, there are no special limitations on the driving type of the second actuator unit according to the present invention. For example, the second actuator unit according to the present invention may be composed of pneumatic, linear actuator, electric motor, etc.

[0055] The connecting part (136a) of the second actuator part (136) is connected to the actuator installation part (111) of the exhaust nozzle housing part (110) by a hinge structure (H) so as to be rotatable.

[0056] Meanwhile, at least one support member (140) is installed in the exhaust nozzle housing member (110), and the support member (140) is installed so that a first rotation axis (C1) and a second rotation axis (C2) can rotate.

[0057] In this embodiment, the support members (140) are composed of a pair and are symmetrically arranged on each side of the exhaust nozzle housing (110).

[0058] Hereinafter, with reference to FIGS. 1 to 6, the operation of the exhaust nozzle structure (100) according to the present embodiment will be described.

[0059] The exhaust nozzle structure (100) according to the present embodiment is applied to a gas turbine engine. Accordingly, by receiving a signal from a control unit (not shown) of a device (aircraft, launch vehicle, etc.) to which the gas turbine engine is applied, the first actuator unit (126) and the second actuator unit (136) are controlled, thereby adjusting the direction of the thrust of the exhaust gas and the exhaust area.

[0060] When the first actuator part (126) is activated, the first rod part (125) moves in a straight line, and accordingly, the first link member (124) rotates around the first rotation axis (C1). As a result, the slider link connecting part (124b) of the first link member (124) rotates, and the first slider link part (123) connected to the slider link connecting part (124b) slides in the first slider guide part (122). When such sliding movement of the first slider link part (123) occurs, the first flap part (121) rotates around the first hinge (121a), and the angle of the first flap part (121) is adjusted. At this time, compressed air is discharged through the first discharge hole (123d) for sliding action in the first slider guide part (122) of the first slider link part (123), and thereby the gap between the lower surface of the first link body part (123b) and the first flap part (121) is maintained. This reduces frictional force during sliding action, allowing for smooth control action, and also performs cooling action by the discharged compressed air. Furthermore, such sliding action of the first slider link part (123) significantly reduces the need for angle re-correction due to mutual movement between the first flap part (121) and the second flap part (131) compared to a fixed link structure.

[0061] Additionally, when the second actuator part (136) is activated, the second rod part (135) moves in a straight line, and accordingly, the second link member (134) rotates around the second rotation axis (C2). As a result, the slider link connecting part (134b) of the second link member (134) rotates, and the second slider link part (133) connected to the slider link connecting part (134b) slides in the second slider guide part (132). When such sliding movement of the second slider link part (133) occurs, the second flap part (131) rotates around the second hinge (131a), and the angle of the second flap part (131) is adjusted. At this time, compressed air is discharged through the second discharge hole (133d) for sliding action in the second slider guide part (132) of the second slider link part (123), and thereby the gap between the lower surface of the second link body part (133b) and the second flap part (131) is maintained. This reduces frictional force during sliding action, allowing for smooth control action, and also performs cooling action by the discharged compressed air. Furthermore, such sliding action of the second slider link part (133) significantly reduces the need for angle re-correction due to mutual movement between the first flap part (121) and the second flap part (131) compared to a fixed link structure.

[0062] In the case of this embodiment, the first actuator section (126) and the second actuator section (136) are arranged in pairs vertically, and the first flap section (121) and the second flap section (131) are also arranged in pairs vertically, so the control section (not shown) of the device (aircraft, launch vehicle, etc.) to which the gas turbine engine is applied can easily adjust the direction of vertical thrust and the exhaust area.

[0063] According to the exhaust nozzle structure (100) of the present embodiment as described above, the direction of the vertical thrust of the gas turbine engine and the exhaust area can be easily adjusted, and the movement control of the first and second flap parts (121) (131) is easy due to the sliding action of the first and second slider link parts (123) (133). In addition, since compressed air is discharged through the first and second discharge holes (123d) (133d) for the sliding action of the first and second slider link parts (123) (133), frictional force can be reduced during the sliding action, so not only is the control action smooth, but a cooling action by the compressed air is also performed.

[0064] Some aspects of the present invention have been described with reference to embodiments illustrated in the accompanying drawings, but this is merely illustrative and will be understood by those skilled in the art that various modifications and equivalent alternative embodiments are possible therefrom. Accordingly, the true scope of protection of the present invention should be determined only by the appended claims. Industrial applicability

[0065] According to one aspect of the present invention, it can be applied to industries that manufacture or use exhaust nozzle structures. Explanation of the symbols

[0066] 100: Exhaust nozzle structure 110: Exhaust nozzle housing 121: First flap section 122: First slider guide section 123: First slider link section 124: First link absence 125: 1st load section 126: 1st actuator section 131: Second flap section 132: Second slider guide section 133: Second slider link section 134: Second link absence 135: 2nd load section 136: 2nd actuator section 140: Support

Claims

Claim 1 Exhaust nozzle housing portion; a first flap portion rotatably installed in the exhaust nozzle housing portion; a first slider guide portion installed in the first flap portion; a first slider link portion sliding in the first slider guide portion; a first link member rotatably connected to the first slider link portion and installed to rotate around a first rotation axis; a first rod portion rotatably connected to the first link member; a first actuator portion moving the first rod portion and rotatably connected to the exhaust nozzle housing portion; a second flap portion rotatably installed in the first flap portion; a second slider guide portion installed in the second flap portion; a second slider link portion sliding in the second slider guide portion; a second link member rotatably connected to the second slider link portion and installed to rotate around a second rotation axis; a second rod portion rotatably connected to the second link member; a second actuator portion moving the second rod portion and rotatably connected to the exhaust nozzle housing portion; An exhaust nozzle structure of a gas turbine engine, comprising at least one support member installed in the exhaust nozzle housing portion, wherein the first rotational shaft and the second rotational shaft are rotatably installed. Claim 2 The exhaust nozzle structure of a gas turbine engine according to claim 1, wherein the first slider link portion comprises: a first air inlet portion for introducing compressed air; and a plurality of first discharge holes formed in a portion facing the first flap portion for discharging the compressed air introduced into the first air inlet portion. Claim 3 The exhaust nozzle structure of a gas turbine engine according to claim 1, wherein the second slider link portion comprises: a second air inlet portion for introducing compressed air; and a plurality of second discharge holes formed in a portion facing the second flap portion for discharging the compressed air introduced into the second air inlet portion.

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