CN112937879B - Power system of double-engine parallel vehicle type turboprop engine - Google Patents
Power system of double-engine parallel vehicle type turboprop engine Download PDFInfo
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- CN112937879B CN112937879B CN202110337606.4A CN202110337606A CN112937879B CN 112937879 B CN112937879 B CN 112937879B CN 202110337606 A CN202110337606 A CN 202110337606A CN 112937879 B CN112937879 B CN 112937879B
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- gas turbine
- turbine engine
- engine
- cooling
- fixing ring
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
- B64D27/02—Aircraft characterised by the type or position of power plant
- B64D27/10—Aircraft characterised by the type or position of power plant of gas-turbine type
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/08—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
- B64D33/10—Radiator arrangement
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F15/00—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion
- F16F15/02—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems
- F16F15/04—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using elastic means
- F16F15/06—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using elastic means with metal springs
- F16F15/067—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using elastic means with metal springs using only wound springs
Abstract
The invention discloses a power system of a double-engine parallel vehicle type turboprop engine, which comprises a protective cover, a groove, a parallel reduction gear box, a propeller, a right diagonal bracing clutch, a left driven straight gear, a right driven straight gear, a parallel driven helical gear, a flange end face and a cooling buffer mechanism. The cooling buffer mechanism is arranged at the upper ends of the first gas turbine engine and the second gas turbine engine, the first gas turbine engine and the second gas turbine engine are connected in series through the first fixing ring and the second fixing ring, so that the first gas turbine engine and the second gas turbine engine are fixed firmly and are not easy to shake due to impact of external force, and meanwhile, the heat transfer at the upper ends of the first gas turbine engine and the second gas turbine engine is accelerated through the circulating cooling mechanism, so that the advantages of stably fixing and cooling the first gas turbine engine and the second gas turbine engine are achieved.
Description
Technical Field
The invention relates to the related field of turboprop engines, in particular to a power system of a turboprop engine of a double-engine concurrent vehicle type.
Background
The turboprop engine is a gas turbine engine commonly used on an airplane, the force generated by the rotation of a propeller is used as the forward propelling force of the airplane, the existing turboprop engine mostly adopts a single-engine fixed-shaft output or a split-shaft output to be connected with the propeller, and if the engine fails, the consequence that the airplane crashes and cannot continue to operate is caused.
When the power system of the existing double-engine concurrent vehicle type turboprop engine is used, two gas turbine engines are often connected through flanges in parallel, but due to the fact that the power system is impacted by airflow, the gas turbine engines can shake and vibrate mutually to influence power output, and the non-combustible gas turbine engines are cooled to influence normal work of the gas turbine engines.
Disclosure of Invention
Therefore, in order to solve the above-mentioned disadvantages, the present invention provides a power system of a turboprop engine of a twin engine parallel vehicle type.
The invention is realized in such a way that a power system of a double-engine parallel-turning type turboprop engine is constructed, the device comprises a protective cover, a groove, a parallel-turning reduction gear box, a propeller, a first gas turbine engine, a second gas turbine engine, a left driving straight gear, a right driving straight gear, a left inclined strut clutch, a right inclined strut clutch, a left driven straight gear, a right driven straight gear, a parallel-turning driven helical gear, a flange end surface and a cooling buffer mechanism, wherein the groove is formed in the front end of the protective cover, the parallel-turning reduction gear box is arranged at the right end in the protective cover, the cooling buffer mechanism is fixedly arranged at the upper ends of the first gas turbine engine and the second gas turbine engine, the cooling buffer mechanism comprises a first fixed ring, a first supporting rod, a connecting plate, a second fixed ring and a second supporting rod, the second gas turbine engine penetrates through the inner side of the first fixed ring, first gas turbine engine runs through in the solid fixed ring of second inboard, connecting plate one end is fixed with the solid fixed ring bottom front end of first to the connecting plate other end and the solid fixed ring top left end fixed connection of second, both sides are provided with first bracing piece and second bracing piece relatively about the connecting plate left end, first bracing piece upper end is rotated with the solid fixed ring bottom front end of first and is connected, the solid fixed ring top left end normal running fit of second bracing piece and second.
Preferably, the right-hand member of the parallel operation reduction gear box is provided with a flange end face, the output end of the parallel operation reduction gear box is connected with the rotation of a propeller, a first gas turbine engine and a second gas turbine engine are oppositely arranged on the front side and the rear side of the left end of the parallel operation reduction gear box, a left driving spur gear is arranged on an output shaft of the first gas turbine engine, a right driving spur gear is arranged on an output shaft of the second gas turbine engine, the left driving spur gear is connected with a left inclined strut clutch arranged in the parallel operation reduction gear box, the left inclined strut clutch is connected with the left driven spur gear left end, the right driving spur gear is connected with a right inclined strut clutch arranged in the parallel operation reduction gear box, the right inclined strut clutch is connected with a right driven spur gear, a parallel operation driven helical gear is arranged inside the parallel operation reduction gear box, the parallel operation driven helical gear is connected with the left driven spur gear, The right driven spur gears are meshed with each other.
Preferably, first solid fixed ring is the same with the second fixed ring structure, first solid fixed ring includes collar, installing frame, circulative cooling mechanism, first lug, second lug and screw rod, the inside second gas turbine engine that has run through of collar, the collar is fixed mutually with the connecting plate upper end, the collar left end is provided with the installing frame, the installing frame internally mounted has circulative cooling mechanism, the collar upper end left and right sides is provided with first lug and second lug relatively, the screw rod runs through in first lug inboardly to screw rod and the inboard screw-thread fit of second lug.
Preferably, the circulative cooling mechanism includes circulating pump, first conveyer pipe, cooling tube, second conveyer pipe and cooling fin, the circulating pump is connected with the inside left end bolted connection of installing frame, both sides are provided with first conveyer pipe and second conveyer pipe relatively around the circulating pump right-hand member, first conveyer pipe is linked together through cooling tube and second conveyer pipe upper end, the cooling tube embedding is installed in the installing frame inside edge, cooling tube and cooling fin upper end are fixed.
Preferably, first bracing piece and second bracing piece structure are the same, first bracing piece includes slope pole, location axle, swing piece, first supporting block, pressure spring, telescopic link and second supporting block, the slope pole passes through the location axle and rotates with the installing frame bottom to be connected, slope pole and swing piece top normal running fit, swing piece rotates with first supporting block front end to be connected, first supporting block middle part is provided with the telescopic link to the pressure spring has been cup jointed to the telescopic link upper end, the telescopic link is fixed mutually with second supporting block front end, and the second supporting block rotates with the upper left end of connecting plate to be connected.
Preferably, the cooling pipes are distributed in a ring shape, and the cooling pipes are distributed along the inner side of the mounting ring.
Preferably, the cooling fin has an elongated shape, and the cooling fin is in contact with the second gas turbine engine upper end surface.
Preferably, the connecting plate is provided with two, and the left side and the right side of the connecting plate are oppositely provided with a first fixing ring and a second fixing ring.
Preferably, two the connecting plate upper end all is provided with first bracing piece and second bracing piece to first bracing piece and second bracing piece are the symmetric form each other and distribute.
Preferably, the tilt lever has a flat rectangular parallelepiped shape, and the swing block is fitted inside the tilt lever.
Preferably, the pressure spring is made of spring steel and has excellent elastic potential energy.
Preferably, the positioning shaft is made of stainless steel and has strong corrosion resistance.
The invention has the following advantages: the invention provides a power system of a turboprop engine of a double-engine concurrent vehicle type through improvement, compared with the same type of equipment, the improvement is as follows:
the method has the advantages that: according to the power system of the double-engine parallel vehicle type turboprop engine, the cooling buffer mechanism is arranged at the upper ends of the first gas turbine engine and the second gas turbine engine, the first gas turbine engine and the second gas turbine engine are connected in series through the first fixing ring and the second fixing ring, so that the first gas turbine engine and the second gas turbine engine are fixed stably and are not prone to being shocked and shaken by external force, and meanwhile, the heat transfer at the upper ends of the first gas turbine engine and the second gas turbine engine is accelerated through the circulating cooling mechanism, so that the advantages that the first gas turbine engine and the second gas turbine engine can be stably fixed and cooled are achieved.
The method has the advantages that: according to the power system of the double-engine parallel vehicle type turboprop engine, the first fixing ring and the second fixing ring are arranged at the upper end of the cooling buffer mechanism, the gas turbine engine is embedded into the inner side of the mounting ring, then the screw rod is rotated clockwise, the screw rod is in threaded transmission on the inner side of the second bump, and the distance between the first bump and the second bump is reduced, so that the mounting ring locks the gas turbine engine, the cooling fin is tightly attached to the surface of the gas turbine engine, and the advantage of rapid mounting and fixing is achieved.
The method has the advantages that: according to the power system of the double-engine parallel vehicle type turboprop engine, the circulating cooling mechanism is arranged at the upper ends of the first fixing ring and the second fixing ring, and cooling liquid in the cooling pipe is circularly conveyed through the circulating pump, so that the heat transfer of the upper end of the gas turbine engine is accelerated by the cooling fin, and the advantage of cooling and radiating the gas turbine engine is achieved.
The advantages are that: according to the power system of the double-engine parallel vehicle type turboprop engine, the first supporting rod and the second supporting rod are arranged at the upper end of the connecting plate, when the upper end of the gas turbine engine generates a deflection force, the inclined rod can swing around the positioning shaft, so that the swinging block drives the first presenting block to press the pressure spring at the upper end of the telescopic rod to generate deformation, the deflection force at the upper end of the gas turbine engine is absorbed, and the advantage that the gas turbine engine can work stably is achieved.
Drawings
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a schematic cross-sectional view of the protective cover of the present invention;
FIG. 3 is a schematic cross-sectional view of a turboprop engine of the present invention;
FIG. 4 is a schematic top view of the cooling buffer mechanism of the present invention;
FIG. 5 is a schematic perspective view of the cooling buffer mechanism of the present invention;
FIG. 6 is a cross-sectional view of a first retaining ring of the present invention;
FIG. 7 is a schematic perspective view of the hydronic cooling mechanism of the present invention;
fig. 8 is a perspective view of the first support rod of the present invention.
Wherein: a protective cover-1, a groove-2, a parallel operation reduction gear box-3, a propeller-4, a first gas turbine engine-5, a second gas turbine engine-6, a left driving spur gear-7, a right driving spur gear-8, a left inclined strut clutch-9, a right inclined strut clutch-10, a left driven spur gear-11, a right driven spur gear-12, a parallel operation driven helical gear-13, a flange end face-14, a cooling buffer mechanism-15, a first fixing ring-151, a first supporting rod-152, a connecting plate-153, a second fixing ring-154, a second supporting rod-155, a mounting ring-1511, a mounting frame-1512, a circulating cooling mechanism-1513, a first lug-1514, a second lug-1515, a screw-1516, a screw rod-13, a screw rod-6, a screw rod-1, a screw rod-9, a screw rod-6, a screw rod-9, a screw rod-6, a screw rod-9, a screw rod-6, a screw rod-9, a screw rod-6, a screw rod, a, The device comprises a circulating pump-15131, a first conveying pipe-15132, a cooling pipe-15133, a second conveying pipe-15134, a cooling fin-15135, an inclined rod-1521, a positioning shaft-1522, a swinging block-1523, a first bearing block-1524, a pressure spring-1525, a telescopic rod-1526 and a second bearing block-1527.
Detailed Description
The present invention will be described in detail below with reference to fig. 1 to 8, and the technical solutions in the embodiments of the present invention will be clearly and completely described, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The first embodiment is as follows:
referring to fig. 1, 2 and 3, the present invention provides a power system of a double-engine parallel vehicle type turboprop engine by improvement, which includes a protective cover 1, a slot 2, a parallel reduction gear box 3, a propeller 4, a first gas turbine engine 5, a second gas turbine engine 6, a left driving spur gear 7, a right driving spur gear 8, a left sprag clutch 9, a right sprag clutch 10, a left driven spur gear 11, a right driven spur gear 12, a parallel driven helical gear 13, a flange end face 14 and a cooling buffer mechanism 15, wherein the front end of the protective cover 1 is provided with the slot 2, the right end inside the protective cover 1 is provided with the parallel reduction gear box 3, the cooling buffer mechanism 15 is fixedly installed at the upper ends of the first gas turbine engine 5 and the second gas turbine engine 6, the right end of the parallel reduction gear box 3 is provided with the flange end face 14, and the output end of the parallel reduction gear box 3 is rotatably connected with the propeller 4, a first gas turbine engine 5 and a second gas turbine engine 6 are oppositely arranged on the front side and the rear side of the left end of the parallel operation reduction gear box 3, a left driving spur gear 7 is arranged on an output shaft of the first gas turbine engine 5, a right driving spur gear 8 is arranged on an output shaft of the second gas turbine engine 6, the left driving spur gear 7 is connected with a left inclined strut clutch 9 arranged in the parallel operation reduction gear box 3, the left inclined strut clutch 9 is connected with the left end of a left driven spur gear 11, the right driving spur gear 8 is connected with a right inclined strut clutch 10 arranged in the parallel operation reduction gear box 3, the right inclined strut clutch 10 is connected with a right driven spur gear 12, a parallel operation driven helical gear 13 is arranged in the parallel operation reduction gear box 3, and the parallel operation driven helical gear 13 is meshed with the left driven spur gear 11 and the right straight gear 12.
Referring to fig. 4 and 5, the present invention provides a power system of a double-engine-car-type turboprop engine by improvement, wherein the cooling buffer mechanism 15 includes a first fixing ring 151, a first supporting rod 152, a connecting plate 153, a second fixing ring 154 and a second supporting rod 155, the second gas turbine engine 6 penetrates through the first fixing ring 151, the first gas turbine engine 5 penetrates through the second fixing ring 154, one end of the connecting plate 153 is fixed to the front end of the bottom of the first fixing ring 151, the other end of the connecting plate 153 is fixedly connected to the left end of the top of the second fixing ring 154, the first supporting rod 152 and the second supporting rod 155 are disposed at the upper and lower sides of the left end of the connecting plate 153, the upper end of the first supporting rod 152 is rotatably connected to the front end of the bottom of the first fixing ring 151, the second supporting rod 155 is rotatably matched to the left end of the top of the second fixing ring 154, the two connecting plates 153 are disposed, the first fixing ring 151 and the second fixing ring 154 are disposed at the left and right sides of the connecting plate 153, two connecting plate 153 upper ends all are provided with first bracing piece 152 and second bracing piece 155 to first bracing piece 152 and second bracing piece 155 are each other the symmetry form and distribute, do benefit to and play the effect of buffering.
Referring to fig. 6, the power system of a double-engine vehicle-type turboprop engine is provided by the present invention through an improvement, the first fixing ring 151 and the second fixing ring 154 have the same structure, the first fixing ring 151 includes a mounting ring 1511, a mounting frame 1512, a circulating cooling mechanism 1513, a first protrusion 1514, a second protrusion 1515 and a screw 1516, the second gas turbine engine 6 penetrates through the inside of the mounting ring 1511, the mounting ring 1511 is fixed to the upper end of the connecting plate 153, the mounting frame 1512 is disposed at the left end of the mounting ring 1511, the circulating cooling mechanism 1513 is mounted inside the mounting frame 1512, the first protrusion 1514 and the second protrusion 1515 are disposed on the left and right sides of the upper end of the mounting ring 1511, the screw 1516 penetrates through the inner side of the first protrusion 1514, and the screw 1516 is in threaded engagement with the inner side of the second protrusion 1515, which is beneficial to adjusting the distance between the first protrusion 1514 and the second protrusion 1515.
Referring to fig. 7, the present invention provides a power system of a twin-engine type turboprop engine by improving, wherein a circulating cooling mechanism 1513 includes a circulating pump 15131, a first delivery pipe 15132, a cooling pipe 15133, a second delivery pipe 15134 and a cooling fin 15135, the circulating pump 15131 is connected with a left bolt inside a mounting frame 1512, the front and rear sides of the right end of the circulating pump 15131 are oppositely provided with the first delivery pipe 15132 and the second delivery pipe 15134, the first delivery pipe 15132 is communicated with the upper end of the second delivery pipe 15134 through the cooling pipe 15133, the cooling pipe 15133 is embedded and mounted on the inner edge of the mounting frame 1511, the cooling pipe 15133 is fixed with the upper end of the cooling fin 15135, the cooling pipe 15133 is distributed in a ring shape, and the cooling tubes 15133 are distributed along the inside of the mounting ring 1511, the cooling fins 15135 are elongated, and cooling fins 15135 contact the upper end surface of second gas turbine engine 6, contributing to the effect of accelerating the heat transfer at the upper end of second gas turbine engine 6.
Referring to fig. 8, the power system of a double engine parallel type turboprop provided herein is improved, the first support rod 152 and the second support rod 155 have the same structure, the first support rod 152 includes an inclined rod 1521, a positioning shaft 1522, a swinging block 1523, a first receiving block 1524, a pressure spring 1525, an expansion rod 1526 and a second receiving block 1527, the inclined rod 1521 is rotatably connected to the bottom of the mounting frame 1512 through the positioning shaft 1522, the inclined rod 1521 is rotatably matched with the top of the swinging block 1523, the swinging block 1523 is rotatably connected to the front end of the first receiving block 1524, an expansion rod 1526 is disposed in the middle of the first receiving block 1524, the pressure spring 5 is sleeved at the upper end of the expansion rod 1526, the expansion rod 1526 is fixed to the front end of the second receiving block 7, the second receiving block 1527 is rotatably connected to the upper left end of the connecting plate 153, the inclined rod 1521 is in a flat rectangular shape, and the swinging block 1523 is embedded inside the inclined rod 1521, thereby facilitating the smooth swinging action of the inclined rod 1521, the pressure spring 1525 is made of spring steel, elastic potential energy is excellent, and the positioning shaft 1522 is made of stainless steel and is high in corrosion resistance.
Example two:
the invention provides a power system of a double-engine concurrent vehicle type turboprop engine by improving, wherein the mounting frame 1512 is in a cylindrical shape with an internal cavity, which is beneficial to the effect of mounting and fixing the circulating pump 15131, and the first fixing ring 151 and the second fixing ring 154 are symmetrically arranged with each other, which is beneficial to the effect of enabling the first gas turbine engine 5 and the second gas turbine engine 6 to be distributed in parallel with each other.
The invention provides a power system of a double-engine concurrent vehicle type turboprop engine through improvement, and the working principle is as follows;
firstly, horizontally placing a double-engine parallel-car turboprop engine before use, and installing the double-engine parallel-car turboprop engine on a proper position at the upper end of an airplane;
secondly, when in use, the gas turbine engine is embedded into the mounting ring 1511, then the screw 1516 is rotated clockwise, the screw 1516 is in threaded transmission inside the second lug 1515, the distance between the first lug 1514 and the second lug 1515 is reduced, so that the mounting ring 1511 locks the gas turbine engine, the cooling fins 15135 are tightly attached to the surface of the gas turbine engine, and the first gas turbine engine 5 and the second gas turbine engine 6 are connected in series;
fourthly, then acquiring the rotating speed Ng of the first gas turbine engine 5 and the second gas turbine engine 6 and the rotating speed Np of the propeller 4 through a rotating speed sensor arranged on the parallel operation reduction gearbox 3, and calculating the current flight speed according to the current rotating speed of the propeller 4;
thirdly, judging whether the current flight speed is less than the specified speed of the low-speed mode or not through a full authority digital engine control system (FADEC); if the speed is lower than the speed specified in the low-speed mode, the oil quantity is increased through the fuel oil regulating valve so as to increase the rotating speed of the first gas turbine engine 5, the left driving spur gear 7 is enabled to be jointed with the left inclined strut clutch 9, the oil quantity is reduced through the fuel oil regulating valve so as to reduce the rotating speed of the second gas turbine engine 6, the right driving spur gear 8 is enabled to be separated from the right inclined strut clutch 10, and the single-engine driving propeller 4 is realized; if the speed is higher than the speed specified in the low-speed mode, the oil quantity is simultaneously increased through the fuel oil regulating valve, the rotating speeds of the first gas turbine engine 5 and the second gas turbine engine 6 are increased, and the left inclined strut clutch 9 and the right inclined strut clutch 10 are connected, so that the double-engine parallel operation driving propeller 4 is realized; simultaneously monitoring the rotating speed and the torque of the propeller 4 so as to obtain the power demand of the propeller 4, and if the power is smaller than the single-engine rated power, reducing the oil quantity through a fuel regulating valve to control the first gas turbine engine 5 to be disengaged from the left inclined strut clutch 9 so as to realize the single-engine driving of the propeller 4; in a failure mode, if one gas turbine engine is damaged and cannot work, the rotating speed of the engine is reduced, the engine is separated from the clutch, and the rest of the engines run normally, so that the single-engine driving propeller 4 is realized, and the short-time running of the airplane is ensured;
fifthly, the cooling liquid in the cooling pipe 15133 is circulated and conveyed by the circulating pump 15131, so that the cooling fins 15135 accelerate the heat transfer at the upper end of the gas turbine engine, and the gas turbine engine can be cooled and radiated;
sixthly, and through having set up first bracing piece 152 and second bracing piece 155 on connecting plate 153, when the gas turbine engine upper end produced the polarized force, can make slope pole 15121 swing around location axle 1522, thereby make swing piece 1523 drive first be a piece 1524 and press the pressure spring 1525 that moves telescopic link 1526 upper end and produce deformation, absorb gas turbine engine upper end polarized force, can make gas turbine engine smooth work.
The invention provides a power system of a turboprop engine of a double-engine concurrent vehicle type through improvement, a cooling buffer mechanism 15 is arranged at the upper ends of a first gas turbine engine 5 and a second gas turbine engine 6, the first gas turbine engine 5 and the second gas turbine engine 6 are coupled in series by the first fixing ring 151 and the second fixing ring 154, so that the first gas turbine engine 5 and the second gas turbine engine 6 are firmly fixed, are not easily shaken by external force, and the first and second support bars 152 and 155 absorb the generated polarization force, while the heat transfer at the upper ends of first gas turbine engine 5 and second gas turbine engine 6 is accelerated by circulating cooling mechanism 1513, the first gas turbine engine 5 and the second gas turbine engine 6 are cooled down, so that the advantages that the first gas turbine engine 5 and the second gas turbine engine 6 can be stably fixed and cooled down are achieved; the first fixing ring 151 and the second fixing ring 154 are arranged at the upper end of the cooling buffer mechanism 15, the gas turbine engine is embedded into the mounting ring 1511, then the screw 1516 is rotated clockwise, the screw 1516 is in threaded transmission inside the second bump 1515, and the distance between the first bump 1514 and the second bump 1515 is reduced, so that the mounting ring 1511 locks the gas turbine engine, the cooling fin 15135 is tightly attached to the surface of the gas turbine engine, and the advantage of quick mounting and fixing is achieved; by arranging the circulating cooling mechanism 1513 at the upper ends of the first fixing ring 151 and the second fixing ring 154, the cooling liquid in the cooling pipe 15133 is circulated and conveyed through the circulating pump 15131, so that the cooling fins 15135 accelerate the heat transfer at the upper end of the gas turbine engine, and the advantage of cooling and radiating the gas turbine engine is achieved; through having set up first bracing piece 152 and second bracing piece 155 on connecting plate 153, when the gas turbine engine upper end produced the polarization force, can make slope pole 15121 swing around location axle 1522 to make swing piece 1523 drive the first pressure spring 1525 that is piece 1524 pressure and moves telescopic link 1526 upper end and produce deformation, absorb gas turbine engine upper end polarization force, reached and to have made the advantage of the steady work of gas turbine engine.
The basic principles and main features of the present invention and the advantages of the present invention have been shown and described, and the standard parts used in the present invention are all available on the market, the special-shaped parts can be customized according to the description and the accompanying drawings, the specific connection mode of each part adopts the conventional means of bolt and rivet, welding and the like mature in the prior art, the machinery, parts and equipment adopt the conventional type in the prior art, and the circuit connection adopts the conventional connection mode in the prior art, and the details are not described herein.
The previous description of the disclosed embodiments is provided to enable any person skilled in the art to make or use the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the invention. Thus, the present invention is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.
Claims (9)
1. A power system of a double-engine parallel-operation turboprop engine comprises a protective cover (1), a groove (2), a parallel-operation reduction gear box (3), a propeller (4), a first gas turbine engine (5), a second gas turbine engine (6), a left driving straight gear (7), a right driving straight gear (8), a left inclined strut clutch (9), a right inclined strut clutch (10), a left driven straight gear (11), a right driven straight gear (12), a parallel-operation driven helical gear (13) and a flange end face (14), wherein the groove (2) is formed in the front end of the protective cover (1), and the parallel-operation reduction gear box (3) is arranged at the right end inside the protective cover (1);
the method is characterized in that: the cooling buffer mechanism (15) is fixedly arranged at the upper ends of the first gas turbine engine (5) and the second gas turbine engine (6), the cooling buffer mechanism (15) comprises a first fixing ring (151), a first supporting rod (152), a connecting plate (153), a second fixing ring (154) and a second supporting rod (155), the second gas turbine engine (6) penetrates through the inner side of the first fixing ring (151), the first gas turbine engine (5) penetrates through the inner side of the second fixing ring (154), one end of the connecting plate (153) is fixed with the front end of the bottom of the first fixing ring (151), the other end of the connecting plate (153) is fixedly connected with the left end of the top of the second fixing ring (154), and the first supporting rod (152) and the second supporting rod (155) are oppositely arranged at the upper side and the lower side of the left end of the connecting plate (153), the upper end of the first supporting rod (152) is rotatably connected with the front end of the bottom of the first fixing ring (151), the second supporting rod (155) is rotatably matched with the left end of the top of the second fixing ring (154), the first supporting rod (152) and the second supporting rod (155) have the same structure, the first supporting rod (152) comprises an inclined rod (1521), a positioning shaft (1522), a swinging block (1523), a first bearing block (1524), a pressure spring (1525), an expansion rod (1526) and a second bearing block (1527), the inclined rod (1521) is rotatably connected with the bottom of the mounting frame (1512) through the positioning shaft (1522), the inclined rod (1521) is rotatably matched with the top of the swinging block (1523), the swinging block (1523) is rotatably connected with the front end of the first bearing block (1524), the expansion rod (1526) is arranged in the middle of the first bearing block (1524), and the upper end of the expansion rod (1526) is sleeved with the pressure spring (1525), the telescopic rod (1526) is fixed with the front end of the second bearing block (1527), and the second bearing block (1527) is rotatably connected with the upper left end of the connecting plate (153).
2. The power system of a twin-engine, twin-: the combined reduction gear box (3) right-hand member is provided with flange terminal surface (14) to the combined reduction gear box (3) output rotates with screw (4) and is connected, both sides are provided with first gas turbine engine (5) and second gas turbine engine (6) relatively around the combined reduction gear box (3) left end, be equipped with left initiative spur gear (7) on first gas turbine engine (5) output shaft, be equipped with right initiative spur gear (8) on second gas turbine engine (6) output shaft, left side initiative spur gear (7) link to each other with left bracing clutch (9) that set up in combined reduction gear box (3), left side bracing clutch (9) are connected with left driven spur gear (11) left end, right side initiative spur gear (8) are connected with right bracing clutch (10) that set up in combined reduction gear box (3), the right inclined strut clutch (10) is connected with a right driven straight gear (12), a parallel operation driven helical gear (13) is arranged inside the parallel operation reduction gear box (3), and the parallel operation driven helical gear (13) is meshed with the left driven straight gear (11) and the right driven straight gear (12) mutually.
3. The power system of a twin-engine, twin-: the first fixing ring (151) and the second fixing ring (154) are identical in structure, the first fixing ring (151) comprises a mounting ring (1511), a mounting frame (1512), a circulating cooling mechanism (1513), a first bump (1514), a second bump (1515) and a screw (1516), a second gas turbine engine (6) penetrates through the mounting ring (1511), the mounting ring (1511) is fixed to the upper end of the connecting plate (153), the left end of the mounting ring (1511) is provided with the mounting frame (1512), the circulating cooling mechanism (1513) is mounted inside the mounting frame (1512), the first bump (1514) and the second bump (1515) are oppositely arranged on the left side and the right side of the upper end of the mounting ring (1511), the screw (1516) penetrates through the inner side of the first bump (1514), and the screw (1516) is in threaded fit with the inner side of the second bump (1515).
4. The power system of a twin-engine, twin-: the circulating cooling mechanism (1513) comprises a circulating pump (15131), a first conveying pipe (15132), a cooling pipe (15133), a second conveying pipe (15134) and cooling fins (15135), the circulating pump (15131) is in bolted connection with the left end inside the installation frame (1512), the first conveying pipe (15132) and the second conveying pipe (15134) are oppositely arranged on the front side and the rear side of the right end of the circulating pump (15131), the first conveying pipe (15132) is communicated with the upper end of the second conveying pipe (15134) through the cooling pipe (15133), the cooling pipe (15133) is embedded and installed on the inner side edge of the installation ring (1511), and the upper ends of the cooling pipe (15133) and the cooling fins (15135) are fixed.
5. The power system of a twin-engine, twin-: the cooling tubes (15133) are distributed in a ring shape, and the cooling tubes (15133) are distributed along the inner side of the mounting ring (1511).
6. The power system of a twin-engine, twin-: the cooling fins (15135) are elongated, and the cooling fins (15135) are in contact with the upper end surface of the second gas turbine engine (6).
7. The power system of a twin-engine, twin-: the number of the connecting plates (153) is two, and a first fixing ring (151) and a second fixing ring (154) are oppositely arranged on the left side and the right side of each connecting plate (153).
8. The power system of a twin engine parallel type turboprop according to claim 7, wherein: two connecting plate (153) upper end all is provided with first bracing piece (152) and second bracing piece (155), and first bracing piece (152) and second bracing piece (155) are the symmetrical form each other and distribute.
9. The power system of a twin-engine, twin-: the tilting lever (1521) is in the shape of a flat rectangular parallelepiped, and the swing block (1523) is fitted inside the tilting lever (1521).
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| CN112937879B true CN112937879B (en) | 2021-11-02 |
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| CN206704534U (en) * | 2017-03-27 | 2017-12-05 | 必扬星环（北京）航空科技有限公司 | Double hair turbine wheel shaft power depopulated helicopters |
| CN206704533U (en) * | 2017-03-27 | 2017-12-05 | 必扬星环（北京）航空科技有限公司 | It is easy to the double hair turbine wheel shaft depopulated helicopter dynamical systems safeguarded |
| CN108238259A (en) * | 2018-02-08 | 2018-07-03 | 天津曙光天成科技有限公司 | A kind of power plant and unmanned helicopter |
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2021
- 2021-03-30 CN CN202110337606.4A patent/CN112937879B/en active Active
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB819489A (en) * | 1955-05-25 | 1959-09-02 | David Wark Hutchinson | Improvements in differentially connected twin turbine power plant |
| DE202013002095U1 (en) * | 2013-03-04 | 2013-03-20 | Hans Schneeweiss | Free-flow turbine plant |
| CN106828906A (en) * | 2017-03-27 | 2017-06-13 | 必扬星环（北京）航空科技有限公司 | Double hair turbine wheel shaft power depopulated helicopters |
| CN106828907A (en) * | 2017-03-27 | 2017-06-13 | 必扬星环（北京）航空科技有限公司 | It is easy to the double hair turbine wheel shaft depopulated helicopter dynamical systems safeguarded |
| CN206704534U (en) * | 2017-03-27 | 2017-12-05 | 必扬星环（北京）航空科技有限公司 | Double hair turbine wheel shaft power depopulated helicopters |
| CN206704533U (en) * | 2017-03-27 | 2017-12-05 | 必扬星环（北京）航空科技有限公司 | It is easy to the double hair turbine wheel shaft depopulated helicopter dynamical systems safeguarded |
| CN108238259A (en) * | 2018-02-08 | 2018-07-03 | 天津曙光天成科技有限公司 | A kind of power plant and unmanned helicopter |
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| CN112937879A (en) | 2021-06-11 |
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Address after: 201611 3 3 Ting Ting Road, Che Dun Town, Songjiang District, Shanghai Patentee after: Shanghai Shangshi aeroengine Co.,Ltd. Address before: 200000 building 3, 199 Maoting Road, Chedun Town, Songjiang District, Shanghai Patentee before: SHANGHAI SHANGSHI ENERGY TECHNOLOGY CO.,LTD. |
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