Ejection cooling structure and engine

Abstract

The present invention provides an ejection cooling structure and an engine, belonging to the technical field of engineering machinery, including: a reducer mounting seat having an installation cavity for installing the reducer; a first end of the exhaust cavity is used to communicate with the outlet of the gas turbine engine, and a second end of the exhaust cavity is connected to the outside atmosphere; a cooling channel is formed in the mounting cavity, the first end of the cooling channel is connected to the first end of the exhaust cavity, and the second end of the cooling channel is connected to the outside atmosphere. When in use, the outside cold air is sucked in from the second end of the cooling channel and transported to the first end by the pressure difference as the driving force, and the cold air takes away the heat from the outer surface of the reducer in the form of convection heat exchange, and the air after absorbing the heat enters the first end of the exhaust cavity, and is mixed with the gas in the exhaust cavity and discharged to achieve the cooling of the reducer. The ejection cooling structure provided by the present invention solves the problem of bleed air from the compressor interstage or outlet of the engine, which reduces the thermal efficiency of the engine and thus increases the fuel consumption of the engine.

Description

Technical Field

[0001] The invention relates to the technical field of engineering machinery, and in particular to an ejection cooling structure and an engine. Background Art

[0002] The shaft power from the free turbine of a propeller engine and a turboshaft engine is used to drive the propeller or rotor to provide power for the aircraft. The speed of the engine's free turbine is relatively high, while the speed of the propeller and rotor is usually an order of magnitude smaller than that of the free turbine, so the speed of the free turbine shaft needs to be reduced by a reducer. A rear-mounted reducer is a more common form. Its advantage is that it is installed close to the free turbine, so the free turbine power output shaft is shorter. Its disadvantage is that the reducer is close to the exhaust pipe at the rear end of the engine, and the temperature is higher, so insulation and cooling measures are required.

[0003] In the prior art, a post-mounted reducer usually draws high-pressure cold air from the compressor stage or outlet of the engine, and transports it to the cavity between the exhaust pipe and the reducer through an external pipeline. The heat of the reducer is removed by convection exchange between the high-pressure cold air and the reducer casing, thereby reducing the temperature of the reducer.

[0004] However, bleed air from the compressor interstage or outlet of the engine reduces the thermal efficiency of the engine and increases the engine fuel consumption. In addition, the additional external bleed air pipeline increases the weight of the engine. Summary of the invention

[0005] Therefore, the technical problem to be solved by the present invention is to overcome the problem that, when cooling the reducer, the gas turbine engine in the prior art draws air from the compressor stage or outlet of the engine, which reduces the thermal efficiency of the engine and increases the fuel consumption of the engine, thereby providing an induced cooling structure and an engine.

[0006] In order to solve the above technical problems, the present invention provides an ejection cooling structure, comprising:

[0007] A reducer mounting seat, having a mounting cavity for mounting the reducer;

[0008] An exhaust chamber, wherein a first end of the exhaust chamber is used to communicate with an outlet of the gas turbine engine, and a second end of the exhaust chamber is communicated with the outside atmosphere;

[0009] A cooling channel is formed between the outer wall of the reducer in the installation cavity and the side wall of the reducer mounting seat, the first end of the cooling channel is connected to the first end of the exhaust cavity, the second end of the cooling channel is provided with an air inlet, and the cooling channel is connected to the outside atmosphere through the air inlet.

[0010] Optionally, the reducer mounting seat is arranged at the tail of the gas turbine engine, and the exhaust chamber is arranged around the reducer mounting seat.

[0011] Optionally, a heat insulation screen is provided on the side wall of the reducer mounting seat.

[0012] Optionally, a plurality of support plates are provided at the first end of the exhaust cavity, and the first end of the cooling channel is connected to the downstream side of the support plates through a first flow channel.

[0013] Optionally, an airflow channel extending radially is formed inside the support plate, an inlet end of the airflow channel is communicated with the first end of the cooling channel, and an outlet end of the airflow channel is communicated with the downstream side of the support plate.

[0014] Optionally, the support plate has an annular cavity in the circumference thereof which is connected to the outlet end of the airflow channel, and the annular cavity has an outlet which is connected to the exhaust cavity and faces the exhaust direction of the exhaust cavity.

[0015] Optionally, the annular cavity has a detachable cover plate, one end of which is suitable for being mounted on the gas turbine engine casing by fasteners, and the other end of the cover plate is overlapped with the outer wall of the exhaust cavity to form an outlet connected to the exhaust cavity.

[0016] Optionally, the cover plate is a ring-shaped bent structure.

[0017] Optionally, the first end of the cooling channel is connected to the upstream side of the support plate through a second flow channel.

[0018] Optionally, a support plate is provided at the end of the first end of the cooling channel, and the support plate has a first through hole communicating with the upstream side of the support plate.

[0019] Optionally, the support plate is inclined radially outwardly toward a direction approaching the gas turbine engine.

[0020] Optionally, a sealing plate is provided at one end of the reducer mounting seat close to the gas turbine engine, and the sealing plate has a second through hole connecting the upstream side of the support plate with the cooling channel.

[0021] Optionally, a gap is formed between the cover plate and the free turbine rotor of the gas turbine engine, and the gap connects the upstream side of the support plate with the cooling channel.

[0022] The present invention provides an engine, comprising: an ejection cooling structure as described in any one of the above schemes.

[0023] The technical solution of the present invention has the following advantages:

[0024] 1. The induced cooling structure provided by the present invention, according to Bernoulli's principle, at any cross section of the same flow tube, the sum of the kinetic energy, potential energy and pressure potential energy of a unit volume of fluid is a constant, that is, the total pressure remains unchanged, and the total pressure is the sum of the static pressure and the dynamic pressure. The combustion gas at the first end of the exhaust chamber has been fully expanded after being output by the gas turbine engine, and the total pressure is close to the atmospheric pressure. The combustion gas has a certain flow rate, so the static pressure at the first end of the exhaust chamber is lower than the atmospheric pressure. The first end of the cooling channel is connected to the first end of the exhaust chamber, so the static pressure at the first end of the cooling channel and the first end of the exhaust chamber are the same, so that a pressure difference is formed between the first end and the second end of the cooling channel, and the pressure difference is used as a driving force to suck in external cold air from the air inlet at the second end of the cooling channel and transport it to the first end. The cold air takes away the heat of the outer surface of the reducer in the mounting cavity of the reducer mounting seat in a convection heat exchange manner, and the air after absorbing the heat enters the first end of the exhaust chamber, is mixed with the combustion gas in the exhaust chamber and discharged, thereby realizing the cooling of the reducer. The induced cooling structure provided by the present invention solves the problem that, when cooling the reducer, air is introduced from the compressor interstage or outlet of the engine in the prior art gas turbine engine, which reduces the thermal efficiency of the engine and increases the fuel consumption of the engine.

[0025] 2. The induced cooling structure provided by the present invention sets a reducer mounting seat at the tail of the gas turbine engine, which can enable the reducer to be installed close to the free turbine rotor of the gas turbine engine, shorten the power output shaft of the free turbine rotor, and set an exhaust cavity circumferentially around the reducer mounting seat. The cooling channel is arranged in a ring around the reducer in the mounting cavity, thereby increasing the heat exchange area and improving the heat exchange efficiency.

[0026] 3. In the induced cooling structure provided by the present invention, the heat insulation screen is arranged on the side wall of the reducer mounting seat, so that the heat insulation screen is located between the reducer and the exhaust chamber, which can block part of the heat radiation of the high-temperature combustion gas in the exhaust chamber to the reducer.

[0027] 4. The induced cooling structure provided by the present invention connects the first end of the cooling channel with the downstream side of the support plate through the first flow channel, so that the air after absorbing heat can enter the first end of the exhaust cavity and be mixed with the combustion gas in the exhaust cavity and discharged, thereby achieving cooling of the reducer.

[0028] 5. The induced cooling structure provided by the present invention connects the first end of the cooling channel with the downstream side of the support plate through the air flow channel extending radially inside the support plate to form a first flow channel, which enables the air after absorbing heat to enter the air flow channel from the first end of the cooling channel, be induced to the first end of the exhaust chamber through the air flow channel, and be mixed with the combustion gas in the exhaust chamber and discharged, thereby achieving cooling of the reducer.

[0029] 6. The induced cooling structure provided by the present invention has an annular cavity connected to the outlet end of the airflow channel, which can maintain the same induced driving pressure difference of each airflow channel. The air after absorbing heat enters the exhaust cavity through the outlet of the annular cavity, and the outlet is facing the exhaust direction of the exhaust cavity, which can make the airflow outlet angle almost the same as the gas flow direction in the exhaust cavity, thereby reducing airflow disturbance.

[0030] 7. The induced cooling structure provided by the present invention has one end of the cover plate fixedly mounted on the gas turbine engine casing to prevent the annular cavity from being connected to the external air so that the pressure in the annular cavity is equal to the atmospheric pressure, thereby preventing a pressure difference from being generated. The other end of the cover plate overlaps the outer wall of the exhaust cavity to form an outlet connected to the exhaust cavity. Therefore, the static pressure in the annular cavity is the same as the static pressure at the first end of the exhaust cavity, that is, the static pressure in the annular cavity is also lower than the atmospheric pressure. Driven by the pressure difference, the cold air absorbs heat and is then induced into the annular cavity, enters the exhaust cavity through the outlet of the annular cavity, and is discharged after being mixed with the fuel gas in the exhaust cavity, thereby achieving cooling of the reducer.

[0031] 8. The induced cooling structure provided by the present invention has a cover plate with an annular bending structure, which can be fixedly connected to the gas turbine engine casing at one end while the other end is overlapped with the outer wall of the exhaust cavity, and the bent structure can resist the pressure of the airflow in the annular cavity.

[0032] 9. The induced cooling structure provided by the present invention connects the cooling channel with the upstream side of the support plate through the second flow channel. The cooperation of the first flow channel and the second flow channel can increase the airflow rate of the induced cold air in the cooling channel and improve the heat exchange efficiency.

[0033] 10. In the induced cooling structure provided by the present invention, the support plate supports the support plate to enhance the stability of the support plate, and the cooling channel is connected to the upstream side of the support plate through the first through hole on the support plate to form a second flow channel. Part of the cold air induced in the cooling channel absorbs heat, enters the upstream side of the support plate through the first through hole, and is mixed with the fuel gas and discharged, thereby cooling the reducer.

[0034] 11. In the induced cooling structure provided by the present invention, the support plate is inclined toward the direction close to the gas turbine engine, which can improve the stability of the support plate compared to a vertical setting.

[0035] 12. The induced cooling structure provided by the present invention separates the reducer and the free turbine rotor of the gas turbine engine through a sealing plate, thereby preventing the rotation of the free turbine rotor from disturbing the airflow in the cooling channel. The cooling channel is connected to the upstream side of the support plate through the second through hole on the sealing plate. Part of the cold air induced in the cooling channel enters the upstream side of the support plate through the first through hole and the second through hole, and is mixed with the fuel gas and discharged, thereby cooling the reducer.

[0036] 13. The induced cooling structure provided by the present invention connects the cooling channel with the upstream side of the support plate through the gap between the sealing plate and the free turbine rotor. Part of the cold air induced in the cooling channel enters the upstream side of the support plate through the gap and is mixed with the fuel gas and discharged, thereby cooling the reducer.

[0037] 14. The engine provided by the present invention has any of the above advantages because it adopts the above-mentioned induced cooling structure. BRIEF DESCRIPTION OF THE DRAWINGS

[0038] In order to more clearly illustrate the specific implementation methods of the present invention or the technical solutions in the prior art, the drawings required for use in the specific implementation methods or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are some implementation methods of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0039] Figure 1 A schematic diagram of an implementation of an ejection cooling structure provided in an embodiment of the present invention;

[0040] Figure 2 for Figure 1 Schematic diagram of the support plate in FIG.

[0041] Figure 3 for Figure 1 A magnified schematic diagram of part A;

[0042] Figure 4 for Figure 2 Schematic diagram of the enlarged portion B.

[0043] Description of reference numerals:

[0044] 1. Installation cavity; 2. Free turbine rotor; 3. Exhaust cavity; 4. Cooling channel; 5. Heat shield; 6. Support plate; 7. Air flow channel; 8. Annular cavity; 9. Cover plate; 10. Gas turbine engine casing; 11. Outer wall; 12. Support plate; 13. First through hole; 14. Closing plate; 15. Second through hole; 16. Air inlet. DETAILED DESCRIPTION

[0045] The technical solution of the present invention will be described clearly and completely below in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0046] In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., indicating the orientation or positional relationship, are based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present invention. In addition, the terms "first", "second", and "third" are used for descriptive purposes only, and cannot be understood as indicating or implying relative importance.

[0047] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0048] In addition, the technical features involved in the different embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0049] This embodiment provides an ejection cooling structure capable of cooling by ejection, which is used to cool the reducer of a gas turbine engine.

[0050] like Figure 1 As shown, a specific implementation of an induced cooling structure provided in this embodiment includes: a reducer mounting seat and an exhaust cavity 3; the reducer mounting seat has a mounting cavity 1 for mounting the reducer; the first end of the exhaust cavity 3 is used to communicate with the outlet of the gas turbine engine, and the second end of the exhaust cavity 3 is connected to the outside atmosphere; a cooling channel 4 is formed between the outer side wall of the reducer in the mounting cavity 1 and the side wall of the reducer mounting seat, the first end of the cooling channel 4 is connected to the first end of the exhaust cavity 3, and the second end of the cooling channel 4 is provided with an air inlet 16, and the cooling channel 4 is connected to the outside atmosphere through the air inlet 16.

[0051] When in use, the reducer is installed in the mounting cavity 1 of the reducer mounting seat. According to the Bernoulli principle, at any cross section of the same flow tube, the sum of the kinetic energy, potential energy and pressure potential energy of the unit volume of fluid is a constant, that is, the total pressure remains unchanged, and the total pressure is the sum of the static pressure and the dynamic pressure. The gas at the first end of the exhaust cavity 3 has been fully expanded after being output by the gas turbine engine, and the total pressure is close to the atmospheric pressure. The gas has a certain flow rate, so the static pressure at the first end of the exhaust cavity 3 is lower than the atmospheric pressure. The first end of the cooling channel 4 is connected to the first end of the exhaust cavity 3, so the static pressure at the first end of the cooling channel 4 and the first end of the exhaust cavity 3 are the same, so that a pressure difference is formed between the first end and the second end of the cooling channel 4. The pressure difference is used as a driving force to inhale and transport the external cold air from the air inlet 16 at the second end of the cooling channel 4 to the first end. The cold air takes away the heat from the outer surface of the reducer in a convection heat exchange manner. The air after absorbing the heat enters the first end of the exhaust cavity 3, and is mixed with the gas in the exhaust cavity 3 and discharged to achieve cooling of the reducer. The induced cooling structure provided in this embodiment solves the problem in the prior art that, when cooling the reducer, air is drawn from the compressor interstage or outlet of the engine, which reduces the thermal efficiency of the engine and increases the fuel consumption of the engine.

[0052] like Figure 1 As shown, in the ejection cooling structure provided in this embodiment, the reducer mounting seat is arranged at the tail of the gas turbine engine, and the exhaust cavity 3 is arranged around the reducer mounting seat. The reducer mounting seat is arranged at the tail of the gas turbine engine, so that the reducer can be installed close to the free turbine rotor 2 of the gas turbine engine, shortening the power output shaft of the free turbine rotor 2, and the exhaust cavity 3 is arranged around the circumference of the reducer mounting seat. The cooling channel 4 is arranged in an annular manner around the reducer in the mounting cavity 1, thereby increasing the heat exchange area and improving the heat exchange efficiency.

[0053] like Figure 1 As shown, in the induced cooling structure provided in this embodiment, a heat shield 5 is provided on the side wall of the reducer mounting seat. The heat shield 5 is provided on the side wall of the reducer mounting seat so that the heat shield 5 is located between the reducer and the exhaust chamber 3, and can block part of the heat radiation of the high-temperature combustion gas in the exhaust chamber 3 to the reducer. In addition, as an alternative embodiment, the heat shield 5 can also be omitted, and the heat of the outer surface of the reducer is only taken away by the induced cold air in the cooling channel 4.

[0054] like Figure 1As shown, in the induced cooling structure provided in this embodiment, a plurality of support plates 6 are provided at the first end of the exhaust cavity 3, and the first end of the cooling channel 4 is connected to the downstream side of the support plate 6 through the first flow channel. The first end of the cooling channel 4 is connected to the downstream side of the support plate 6 through the first flow channel, so that the air after absorbing heat can enter the first end of the exhaust cavity 3, be mixed with the fuel gas in the exhaust cavity 3 and be discharged, so as to achieve the cooling of the reducer. In addition, as an alternative embodiment, the support plate 6 can be omitted, and an air flow hole is provided on the inner secondary wall of the first end of the exhaust cavity 3, and the first end of the cooling channel 4 is connected to the first end of the exhaust cavity 3 through the air flow hole.

[0055] like Figure 1 , Figure 2 As shown, in the induced cooling structure provided in this embodiment, an airflow channel 7 extending radially is formed inside the support plate 6, the inlet end of the airflow channel 7 is communicated with the first end of the cooling channel 4, and the outlet end of the airflow channel 7 is communicated with the downstream side of the support plate 6. The airflow channel 7 extending radially inside the support plate 6 makes the first end of the cooling channel 4 communicate with the downstream side of the support plate 6 to form the first flow channel, so that the air after absorbing heat can enter the airflow channel 7 from the first end of the cooling channel 4, be induced to the first end of the exhaust chamber 3 through the airflow channel 7, and be mixed with the fuel gas in the exhaust chamber 3 and discharged, so as to achieve the cooling of the reducer.

[0056] like Figure 1 , Figure 3 As shown, in the induced cooling structure provided in this embodiment, the support plate 6 has an annular cavity 8 in the circumference thereof which is connected to the outlet end of the airflow channel 7, and the annular cavity 8 has an outlet which is connected to the exhaust chamber 3 and faces the exhaust direction of the exhaust chamber 3. The annular cavity 8 is connected to the outlet end of the airflow channel 7, which can keep the induced driving pressure difference of each airflow channel 7 the same, and the air after absorbing heat enters the exhaust chamber 3 through the outlet of the annular cavity 8, and the outlet faces the exhaust direction of the exhaust chamber 3, which can make the airflow exit angle almost the same as the gas flow direction in the exhaust chamber 3, thereby reducing airflow disturbance. In addition, as an alternative embodiment, the annular cavity 8 can be omitted, and the airflow channel 7 of the support plate 6 is directly connected to the first end of the exhaust chamber 3.

[0057] like Figure 1 , Figure 3As shown, in the induced cooling structure provided in this embodiment, the annular cavity 8 has a detachable cover plate 9, one end of which is suitable for being mounted on the gas turbine engine casing 10 by fasteners, and the other end of the cover plate 9 is overlapped with the outer wall 11 of the exhaust cavity 3 to form an outlet communicating with the exhaust cavity 3. One end of the cover plate 9 is fixedly mounted on the gas turbine engine casing 10 to prevent the annular cavity 8 from being connected to the outside air, resulting in the pressure in the annular cavity 8 being equal to the atmospheric pressure, thereby preventing the pressure difference from being generated. The other end of the cover plate 9 overlaps with the outer wall 11 of the exhaust cavity 3 to form an outlet communicating with the exhaust cavity 3, so that the static pressure in the annular cavity 8 is the same as the static pressure at the first end of the exhaust cavity 3, that is, the static pressure in the annular cavity 8 is also lower than the atmospheric pressure. Driven by the pressure difference, the cold air absorbs heat and is induced into the annular cavity 8, enters the exhaust cavity 3 through the outlet of the annular cavity 8, and is mixed with the gas in the exhaust cavity 3 and discharged, thereby achieving the cooling of the reducer. In addition, as an alternative embodiment, the cover plate 9 can be omitted, and an extended edge is provided at the end of the outer wall 11 of the exhaust chamber 3, the extended edge is connected to the gas turbine engine casing 10, and the extended edge is spaced apart from the support plate 6 to form the annular cavity 8 and the outlet into the exhaust chamber 3.

[0058] like Figure 3 As shown, in the induced cooling structure provided in this embodiment, the cover plate 9 is an annular bending structure. The cover plate 9 of the annular bending structure can overlap and cooperate with the outer wall 11 of the exhaust cavity 3 at the other end when one end is fixedly connected to the gas turbine engine casing 10, and the bent structure can resist the pressure of the airflow in the annular cavity 8. In addition, as an alternative embodiment, the cover plate 9 can also be set to a bending structure that bulges toward the outside, or other shapes that can ensure overlap with the outer wall 11 of the exhaust cavity 3 and have a gap with the support plate 6.

[0059] like Figure 1 As shown, in the induced cooling structure provided in this embodiment, the first end of the cooling channel 4 is connected to the upstream side of the support plate 6 through the second flow channel. The cooling channel 4 is connected to the upstream side of the support plate 6 through the second flow channel. The cooperation of the first flow channel and the second flow channel can increase the airflow rate of the induced cold air in the cooling channel 4 and improve the heat exchange efficiency. In addition, as an alternative embodiment, the second flow channel can be omitted, and the cooling channel 4 and the exhaust chamber 3 are connected only through the first flow channel.

[0060] like Figure 1 , Figure 4As shown, in the induced cooling structure provided in this embodiment, a support plate 12 is provided at the end of the first end of the cooling channel 4, and the support plate 12 has a first through hole 13 connected to the upstream side of the support plate 6. The support plate 12 supports the support plate 6 to enhance the stability of the support plate 6, and the cooling channel 4 is connected to the upstream side of the support plate 6 through the first through hole 13 on the support plate 12 to form the second flow channel. After absorbing heat, part of the cold air induced in the cooling channel 4 enters the upstream side of the support plate 6 through the first through hole 13 and is mixed with the fuel gas and discharged, thereby cooling the reducer.

[0061] like Figure 1 , Figure 4 As shown, in the ejection cooling structure provided in this embodiment, the support plate 12 is inclined radially outward toward the direction close to the gas turbine engine. The support plate 12 is inclined toward the direction close to the gas turbine engine, which can improve the stability of the support plate 6 compared to a vertical arrangement. In addition, as an alternative embodiment, the support plate 12 can also be arranged vertically.

[0062] like Figure 1 , Figure 4 As shown, in the induced cooling structure provided in this embodiment, a sealing plate 14 is provided at one end of the reducer mounting seat close to the gas turbine engine, and the sealing plate 14 has a second through hole 15 connecting the upstream side of the support plate 6 with the cooling channel 4. The reducer and the free turbine rotor 2 of the gas turbine engine are separated by the sealing plate 14 to prevent the rotation of the free turbine rotor 2 from disturbing the airflow in the cooling channel 4. The cooling channel 4 is connected to the upstream side of the support plate 6 through the second through hole 15 on the sealing plate 14. After absorbing heat, part of the cold air induced in the cooling channel 4 enters the upstream side of the support plate 6 through the first through hole 13 and the second through hole 15, and is mixed with the fuel gas and discharged, thereby cooling the reducer. In addition, as an alternative embodiment, the sealing plate 14 can also be omitted, and the free turbine rotor 2 is separated from the reducer by the support plate 12.

[0063] like Figure 1 , Figure 4 As shown, in the induced cooling structure provided in this embodiment, a gap is formed between the sealing plate 14 and the free turbine rotor 2 of the gas turbine engine, and the gap connects the upstream side of the support plate 6 and the cooling channel 4. The cooling channel 4 is connected to the upstream side of the support plate 6 through the gap between the sealing plate 14 and the free turbine rotor 2. After absorbing heat, part of the cold air induced in the cooling channel 4 enters the upstream side of the support plate 6 through the gap and is mixed with the fuel gas and discharged, thereby cooling the reducer.

[0064] How it works

[0065] like Figure 1 As shown, the induced cooling structure provided in this embodiment, when in use, uses the pressure difference between the first end and the second end of the cooling channel 4 as a driving force to suck in external cold air from the second end of the cooling channel 4 and transport it to the first end, and the cold air takes away the heat from the outer surface of the reducer in a convection heat exchange manner, and the air that partially absorbs the heat is transported to the annular cavity 8 through the air flow channel 7 on the support plate 6, and enters the downstream side of the support plate 6 in the exhaust cavity 3 through the outlet of the annular cavity 8, and the air that partially absorbs the heat passes through the first through hole 13 on the support plate 12 and the second through hole 15 on the sealing plate 14, and enters the upstream side of the support plate 6 in the exhaust cavity 3 through the gap between the sealing plate 14 and the free turbine rotor 2, and the air that absorbs the heat is mixed with the fuel gas in the exhaust cavity 3 and discharged, thereby achieving cooling of the reducer.

[0066] In addition, this embodiment also provides an engine, which adopts the one-shot cooling structure described in the above embodiment to achieve cooling of the rear-mounted reducer.

[0067] Obviously, the above embodiments are merely examples for clear explanation, and are not intended to limit the implementation methods. For those skilled in the art, other different forms of changes or modifications can be made based on the above description. It is not necessary and impossible to list all the implementation methods here. The obvious changes or modifications derived from these are still within the scope of protection of the present invention.

Claims

1. An ejection cooling structure, characterized in that: include: A reducer mounting seat having a mounting cavity (1) for mounting the reducer; An exhaust chamber (3), a first end of the exhaust chamber (3) being connected to an outlet of the gas turbine engine, and a second end of the exhaust chamber (3) being connected to the outside atmosphere; A cooling channel (4) is formed between the outer wall of the reducer in the installation cavity (1) and the side wall of the reducer installation seat, the first end of the cooling channel (4) is in communication with the first end of the exhaust cavity (3), the second end of the cooling channel (4) is provided with an air inlet (16), the cooling channel (4) is in communication with the outside atmosphere through the air inlet (16), and the outside cold air is sucked in from the air inlet (16) at the second end of the cooling channel (4) and transported to the first end; A plurality of support plates (6) are provided at the first end of the exhaust cavity (3); the first end of the cooling channel (4) is in communication with the downstream side of the support plate (6) via a first flow channel; the first end of the cooling channel (4) is in communication with the upstream side of the support plate (6) via a second flow channel; An airflow channel (7) extending radially is formed inside the support plate (6), an inlet end of the airflow channel (7) is communicated with a first end of the cooling channel (4), and an outlet end of the airflow channel (7) is communicated with a downstream side of the support plate (6); A support plate (12) is provided at the end of the first end of the cooling channel (4), and the support plate (12) has a first through hole (13) communicating with the upstream side of the support plate (6); A sealing plate (14) is provided at one end of the reducer mounting seat close to the gas turbine engine, and the sealing plate (14) has a second through hole (15) connecting the upstream side of the support plate (6) and the cooling channel (4); The support plate (6) has an annular cavity (8) in the circumference thereof which is in communication with the outlet end of the air flow channel (7); the annular cavity (8) has an outlet which is in communication with the exhaust cavity (3) and faces the exhaust direction of the exhaust cavity (3).

2. The induced cooling structure according to claim 1, characterized in that: The reducer mounting seat is arranged at the tail of the gas turbine engine, and the exhaust chamber (3) is arranged around the reducer mounting seat.

3. The induced cooling structure according to claim 2, characterized in that: A heat insulation screen (5) is provided on the side wall of the reducer mounting seat.

4. The induced cooling structure according to claim 1, characterized in that: The annular cavity (8) has a detachable cover plate (9), one end of the cover plate (9) being suitable for being mounted on a gas turbine engine casing (10) via a fastener, and the other end of the cover plate (9) being overlapped with an outer wall (11) of the exhaust cavity (3) to form an outlet communicating with the exhaust cavity (3).

5. The induced cooling structure according to claim 4, characterized in that: The cover plate (9) is a ring-shaped bent structure.

6. The induced cooling structure according to claim 1, characterized in that: The support plate (12) is inclined radially outward in a direction approaching the gas turbine engine.

7. The induced cooling structure according to claim 1, characterized in that: A gap is formed between the sealing plate (14) and the free turbine rotor (2) of the gas turbine engine, and the gap connects the upstream side of the support plate (6) and the cooling channel (4).

8. An engine, characterized in that: include: The induced cooling structure according to any one of claims 1 to 7.

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