Abstract
A planetary gear transmission for use in turbine engines gas What is provided includes a gearbox housing attached to the engine housing, and a gear ring fixed to the interior of the housing gearbox in a cavity defined therein. A first planetary gear set stage is provided in the housing and including a first gear Sun coupled to an output shaft of the engine, and first planetary gear carrier is rotatably mounted in the housing. First planetary pinion gears are supported by the first gear carrier and mesh with the first sun gear and the ring gear. A second planetary gear set stage is provided within the housing and comprising a second gear Sun Coupled with the first planetary carrier. The second stage planetary gear set includes one second planetary carrier coupled to a propeller shaft. The second carrier supports planetary pinion gears meshing with the ring gear and the second gun gear. The first or second planetary gear carriers are redeemable by a similar carrier with gear arrangement planetary pinion effective to provide reverse rotation of the propeller shaft.
Description
Background of the Invention
1. Field of the Invention
The present invention relates to a planetary gear system, and more particularly to a planetary gear system used in gas turbine engines.
Two. Description of the Prior Art
In the field of propeller-powered aircraft gas turbine and, specifically, where two or more motors used, it is desirable in some aircraft to propellers on each side of the fuselage rotating in opposite directions. Since the turbine engine has a standard rotation direction, which is necessary for those applications to provide different gear reduction transmissions to a specific pair of gas turbine engines used on the same aircraft. Often, this means that the turbine engine has a reverse transmission can take a gearbox which is heavier than the rotation transmission standard on the other motor. Moreover, the gear ratios are usually different and thus the rotational speed of each motor is different. Since the transmission of each motor in a pair in a plane is of a different design, the reliability of the transmission may be different, requiring different parts, etc.
As can be seen, the need for standard rotation and reverse rotation transmission identical motors used for feeding the helices in a single aircraft, requires a substantial inventory since transmissions are intended to be mounted at the manufacturer's plant rather than in the field.
Additionally, each aircraft engines must be regulated independently in the light of the difference in weight and sometimes different rpm propellers due to the different transmissions
.
SUMMARY OF THE INVENTION
An object of the present invention is to provide a planetary gear transmission for use in gas turbine engines that can be adapted from the standard rotation to reverse rotation by replacing interchangeably support one of the stages of transmission.It is a further object of the present invention to provide a motor with a planetary gear transmission that can be converted from a standard rotation to reverse rotation with minimal inventory and wherein the conversion standard for reverse rotation rotation can be done in the field.
It is a further object of the present invention to provide a planetary gear transmission having the two-stage reduction, wherein either the planet stages can be changed by a step similar planetary gear provide reverse rotation without changing the relationship of transmission gear or the weight thereof.
In a construction according to the present invention provides a planetary gear transmission for use in gas turbine engines, including a casing the gearbox attached to the motor housing and a ring gear fixed to the inside of the housing into a cavity defined thereby. A first stage planetary gear set is provided in the housing, including a first sun gear coupled to an engine output shaft and a first planet carrier rotatably mounted in the housing. First planetary pinion gears are supported by the first carrier and mesh with the first sun gear and the ring gear. A second stage planetary gear set is provided within the housing and comprises a second sun gear coupled to the first planet carrier. The second stage planetary gear set includes a second planetary carrier coupled to a propeller shaft. The second carrier supports planetary pinion gears meshing with the ring gear and the second sun gear. The first or second planetary carrier is exchangeable for a similar vehicle with a pinion planetary gear arrangement effective for providing the reverse rotation of the propeller shaft.
More specifically, the first and second planetary carriers are arranged to rotate the propeller shaft in the standard or the same direction as the motor shaft, and a first or second carrier is provided with similar additional planet gears meshing with the pinion planetary pinion gears and the ring gear to provide the rotation to the respective planetary carrier. In the similar carrier, the planetary pinion gears are smaller and engaged with the sun gear while the supplementary pinion gears mesh with smaller planetary gears with the ring gear.
Similarly planet carrier with planetary pinion gears and the pinion gears is complementary radial dimension and the same mass as the planetary carrier it replaces, so that the total mass of the planetary gear transmission adapted for reverse rotation is the same as the mass of the planetary gear transmission arranged for rotation standard. Moreover, in the planetary carrier similar, the planetary pinion gears and supplementary gears are selected so that the effective transmission ratio of the planetary gear transmission resulting for the reverse rotation is the same as the arrangement of planetary gear transmission standard rotation.
The advantages of the above provision are substantial. Thus a gas turbine engine for driving a propeller can become standard in the field of reverse rotation and vice versa. All that is required is the provision of planetary carriers that correspond to either the first or second stage and being adapted to provide reverse rotation as described above. The housing can be divided into the ring gear so that the removal of part of the housing, the first and second planetary stages are exposed, allowing the exchange of the respective planetary carriers. This allows aircraft operators to maintain a smaller inventory of spare engines and / or complete transmissions. Moreover, since a pair of motors with transmissions described herein, although conversely, be balanced in terms of mass and in terms of rpm resulting from the propellers, it simplifies the set up of a pair engine aircraft.
A further improvement is included in this document is the provision of the provisions of auxiliary drive gear must be converted when the planetary gear transmission is reversed. The auxiliary drives or accessories are usually perpendicular to the main propeller shaft and each includes an attachment shaft mounted in suitable bearings and driven bevel gears, one of which is mounted on the attachment shaft and the other of which is mounted on the propeller shaft. In the case of reversing the rotation of the propeller shaft, the bevel gear disposed on the drive shaft 180 rotates must be reversed in its normal direction.
Has been the practice to mount such bevel gears in the drive shaft in a manner that does not allow axial expansion or contraction of the drive shaft though the deflection of the same are compensated. In the present invention, the bevel gear is mounted on the propeller shaft via a spline connection and the housing is supported by suitable bearings.
BRIEF DESCRIPTION OF THE DRAWINGS
Having thus generally described the nature of the invention, reference is now made to the accompanying drawings, showing by way of illustration a preferred embodiment thereof, and in which:
. Figure 1 is an axial view taken through the planetary gear transmission of the second stage for converting the reverse rotation;
. Figure 2 is a schematic view of the planetary gears of the first stage slightly taken along line 2 - 2 of FIG. 1;
. Figure 3 is a schematic view of the planetary gears of the second stage somewhat taken along line 4 - 4 in Fig. 1 but showing the planetary gears rotatably disposed standard;
. Figure 4 is a somewhat schematic view along line 4 - 4 in Fig. 1, showing the gears in the arrangement of FIG. 1 for reverse rotation;
. Figure 5 is a fragmentary axial cross section of a further detail of the present invention;
. Figure 6 is a fragmentary view similar to FIG. 5 showing the state of the art;
. 7 is a fragmentary axial cross section of a detail of another embodiment of the present invention, and
. Figure 8 is a fragmentary schematic view of the planetary gear along line 2 - 2 of FIG. 1 showing the first stage in a reverse rotation.
Description of the Preferred Embodiments
Referring now to the drawings and especially to FIG. 1, there is shown the gear box of a gas turbine engine adapted to drive a propeller. The planetary gear assembly 10 which forms the gear box includes a housing assembly 12 formed by supports 14 and 16 are held together along the flanges 18 and 20 by bolts 22. A ring gear 24 extends around the cavity formed by the housing assembly 12 and includes a flange 26 which is securely held between the flanges 18 and 20 of the shells 14 and 16 by bolts 22. The ring gear 24 has a first stage portion 28 with helical grooves and a second portion of the stage 30 with the gear teeth. An output shaft 32 of the gas turbine engine 1 is shown schematically at one end thereof and a propeller shaft 34 is illustrated at the other end of the housing.
A planetary gear 36 is coupled to the output shaft 32. The sun gear includes a cylindrical extension 38, as shown in Fig. 1. A first integrated carrier phase 40 is provided in the first stage, and includes a cylindrical extension 42 mounted in housing 16 by bearings 43. The first stage carrier 40 includes a pair of hubs 44 and 48. Within the hub 44 is provided an oil passage 46 to lead lubricating oil to the gears, as will be described.
In the first stage, as shown in Fig. 2, three gears 64 mounted on a support 40.
The gear 64 is mounted in the following manner: A sprocket bolt 50 extends between the hubs 44 and 48 and presses as cylindrical magazine 60. A bolt 70 secures the magazine 60 to the hubs 44 and 48 and also coupled to the caps 52 and 54, respectively. Is the bolt head 58 and nut 56 press against the end caps 54 and 52 which in turn is compressed axially in the stud 60. This magazine 60 is slightly longer than the width of the centers 44 and 48. Therefore, the hubs 44 and 48 are not pre-loaded. Each gear 64 is mounted in a journal 60 and a bearing metal bearing 62 is provided to allow the gear 64 to rotate with minimal friction in the journal 60. Lubrication passageway 46 enter the space formed by the cylindrical magazine 60 and caps 52 and 54 and passes through the filters 68 through conduits 66 in the magazine 60 in the area of bearing metal.
Each of the three gears 64 having gear teeth 72 which mesh with the sun gear 36 and ring gear 74. The ring gear 74 is helically grooved portion of the ring gear 28 in order to allow the ring gear 74 to have axial movement, so that as the load increases or decreases, which in turn reacts in the Hydraulic diaphragm 65.
A splined coupling 76 is provided in the center of the first stage and extends into the second stage area. The coupling spline 76 includes a spline coupling segment 78 of the hub extension 48 of the holder 40.
A sun gear 82 is provided in the second stage with internal spline 83 engaged by the gear segment 80 of the coupling 76.
The second stage is shown in Fig. 1 provides for reverse rotation. Therefore, the gears 94 are provided with gears 96 and 94 engage the ring gear portion 30, on one hand, and meshing with gears 96, on the other side. The planetary gears 96 engage the sun gear 82.
The carrier 86 in the second stage of assembly is shown so the combination of gears for reverse rotation. The gears are mounted on the holder 86 in a manner identical to the assembly described with respect to the gears 64 and carrier 40. The carrier 86 includes hubs 88 and 90 over 92.
Gear 96, shown in Fig. 1 is identified with identical numbers to numbers used with respect to the gear 64, but raised by 100. As shown, both carriers 86 and 40 are cantilever type carriers, and the carrier 86 has a splined extension 87 to the propeller shaft 34.
. Figure 3 illustrates the second stage of rotation setting standard comprises five gears 96a to 30 mesh and the crown gear 82. Therefore, in the standard rotation, a sun gear 36 rotates the planetary gears 64 against the stationary ring gear 74, causing the carrier 40 to rotate in the same direction as the sun gear.
Coupling toothing 76 transfers this rotation of sun gear 82. If the second stage is composed of gears 96a, as shown in Fig. 3, below, similarly sun gear 82 rotates the gears 96a against the ring gear 30, causing the bracket 86 to rotate in the same direction as the sun gear 84 and the output shaft 32. If however, reverse rotation is required, the second stage carrier 86 is replaced by a carrier 86 having a combination of gears illustrated by the gears 94 and 96. The gears 94 and 96 are selected such that are reasonably equivalent to the weight of gears 96a from ten gear must be provided in a reverse configuration instead of the five gears in the standard configuration of rotation of the figure. Three. Moreover, the gears are selected so that the transmission ratio is the same whether it is the standard configuration of rotation of the figure. 3 to the configuration of the reverse rotation of the figure. April. The carriers 86 are identical, except that the machining is different in the region of the gears. Therefore, one physically the same for the reverse rotation, except for the additional machining required because the added amount of gearing.
In the case of reverse rotation the configuration as shown in FIGS. 1 and 4, the sun gear 82 rotates gear 96 which in turn rotates gear 94 in the reverse direction against the sun gear 36 and the resulting rotation is reversed such that the carrier 86 rotates in a reverse direction from the sun gear 82 and the output shaft 32. Since the carrier 86 is connected in a spline to the propeller shaft 34, the shaft 34 will rotate in the same direction as the carrier 86 which is opposite to the rotation axis 32.
Two-stage transmission is shown in Fig. 1 significantly reduces the rotation thereof for high torque. For example, where the output shaft of the gas turbine may spin at 30,000 rpm, the propeller shaft 34, given the configuration shown in this application, to rotate at about 1600 rpm
In operation, it is noted that although the second stage has been described in terms of normal or reverse rotation, it may be that the first phase is used for providing reverse rotation. It would actually be even easier to use from the first stage of the first stage in this case has only three gears and therefore the reverse configuration would fixed gears. . Figure 8 shows the planetary gears arranged to reverse rotation of the first stage. Therefore, the gears 65 and 67 replace gear 64 in this case.
In any case, when switching the rotation of a motor in particular, pins 22 are removed to thereby separate the housing 14 of the housing 16. The ring gear 24 can be easily removed from the first stage, due to the splined connection between the ring gear 74 and the ring gear segment 28. The carrier 86 or 40, as the case may be, are then replaced by one with standard or reverse configuration.
As shown in the figure. 5, there is an attachment shaft 228 which is driven by the propeller shaft 34. If given the configuration of rotation to the shaft 34, the drive shaft should be amended 228 accessory. Therefore, the bevel gear 222 which is mounted in a bearing 214 via bearings 212 on the housing assembly 210, must be removed and turned 180 which is mounted in bearing 214 in the case of the present invention is driven by a toothed ring 216 mounted on the shaft 34 via the lock nut 218 which is threaded into the threads 220. The toothed ring 216 must also be changed in the case of reverse rotation. A toothed ring 216 is provided with grooves 224 which engages with the bevel gear 222. The bevel gear 222 has teeth 226 which mesh with teeth 234 on the crown gear 230 fixed to shaft 228 through the cylindrical extension 232 and bearing sleeve articulated 233.
An advantage of this configuration is that the bevel gear 222 is mounted on the housing and on the shaft 34 as has been done previously, as shown in Fig. 6 showing the prior art. In this case, the bevel gear 250, as shown, is mounted directly on the shaft 34. Any axial expansion or retraction of the shaft causes the bevel gear 250 to join or loosen against the sprocket 254. In the present invention, the grooves 224 allow for the axial clearance in relation to the bevel gear 222.
. Figure 7 of the drawings shows another embodiment of the gears 94 and 96. Empirically, it has been determined that the ratio of length to diameter of a gear should not exceed 0860. This relationship takes into account the deviation, the contact teeth, reliability, durability, etc. To overcome this engagement and to comply with the relation mentioned above, the gears 96 and 94 may be bent, as shown in Figure . 7, for example, the gears 294a and 294b that can be, but not necessarily, separated by a spacer 295. Since the gear cylinder is mounted on the magazine 60 in the case of FIG. 1 and 260 in the case of FIG. 7, the rest of the gear assembly does not change even though the cylinder gear itself can be duplicado.Descripción
Background of the Invention
1. Field of the Invention
The present invention relates to a planetary gear system, and more particularly to a planetary gear system used in gas turbine engines.
Two. Description of the Prior Art
In the field of propeller-powered aircraft gas turbine and, specifically, where two or more motors used, it is desirable in some aircraft to propellers on each side of the fuselage rotating in opposite directions. Since the turbine engine has a standard rotation direction, which is necessary for those applications to provide different gear reduction transmissions to a specific pair of gas turbine engines used on the same aircraft. Often, this means that the turbine engine has a reverse transmission can take a gearbox which is heavier than the rotation transmission standard on the other motor. Moreover, the gear ratios are usually different and thus the rotational speed of each motor is different. Since the transmission of each motor in a pair in a plane is of a different design, the reliability of the transmission may be different, requiring different parts, etc.
As can be seen, the need for standard rotation and reverse rotation transmission identical motors used for feeding the helices in a single aircraft, requires a substantial inventory since transmissions are intended to be mounted at the manufacturer's plant rather than in the field.
Additionally, each aircraft engines must be regulated independently in the light of the difference in weight and sometimes different rpm propellers due to the different transmissions.
SUMMARY OF THE INVENTION
An object of the present invention is to provide a planetary gear transmission for use in gas turbine engines that can be adapted from the standard rotation to reverse rotation by replacing interchangeably support one of the stages of transmission.
It is a further object of the present invention to provide a motor with a planetary gear transmission that can be converted from a standard rotation to reverse rotation with minimal inventory and wherein the conversion standard for reverse rotation rotation can be done in the field.
It is a further object of the present invention to provide a planetary gear transmission having the two-stage reduction, wherein either the planet stages can be changed by a step similar planetary gear provide reverse rotation without changing the relationship of transmission gear or the weight thereof.
In a construction according to the present invention provides a planetary gear transmission for use in gas turbine engines, including a casing the gearbox attached to the motor housing and a ring gear fixed to the inside of the housing into a cavity defined thereby. A first stage planetary gear set is provided in the housing, including a first sun gear coupled to an engine output shaft and a first planet carrier rotatably mounted in the housing. First planetary pinion gears are supported by the first carrier and mesh with the first sun gear and the ring gear. A second stage planetary gear set is provided within the housing and comprises a second sun gear coupled to the first planet carrier. The second stage planetary gear set includes a second planetary carrier coupled to a propeller shaft. The second carrier supports planetary pinion gears meshing with the ring gear and the second sun gear. The first or second planetary carrier is exchangeable for a similar vehicle with a pinion planetary gear arrangement effective for providing the reverse rotation of the propeller shaft.
More specifically, the first and second planetary carriers are arranged to rotate the propeller shaft in the standard or the same direction as the motor shaft, and a first or second carrier is provided with similar additional planet gears meshing with the pinion planetary pinion gears and the ring gear to provide the rotation to the respective planetary carrier. In the similar carrier, the planetary pinion gears are smaller and engaged with the sun gear while the supplementary pinion gears mesh with smaller planetary gears with the ring gear.
Similarly planet carrier with planetary pinion gears and the pinion gears is complementary radial dimension and the same mass as the planetary carrier it replaces, so that the total mass of the planetary gear transmission adapted for reverse rotation is the same as the mass of the planetary gear transmission arranged for rotation standard. Moreover, in the planetary carrier similar, the planetary pinion gears and supplementary gears are selected so that the effective transmission ratio of the planetary gear transmission resulting for the reverse rotation is the same as the arrangement of planetary gear transmission standard rotation.
The advantages of the above provision are substantial. Thus a gas turbine engine for driving a propeller can become standard in the field of reverse rotation and vice versa. All that is required is the provision of planetary carriers that correspond to either the first or second stage and being adapted to provide reverse rotation as described above. The housing can be divided into the ring gear so that the removal of part of the housing, the first and second planetary stages are exposed, allowing the exchange of the respective planetary carriers. This allows aircraft operators to maintain a smaller inventory of spare engines and / or complete transmissions. Moreover, since a pair of motors with transmissions described herein, although conversely, be balanced in terms of mass and in terms of rpm resulting from the propellers, it simplifies the set up of a pair engine aircraft.
A further improvement is included in this document is the provision of the provisions of auxiliary drive gear must be converted when the planetary gear transmission is reversed. The auxiliary drives or accessories are usually perpendicular to the main propeller shaft and each includes an attachment shaft mounted in suitable bearings and driven bevel gears, one of which is mounted on the attachment shaft and the other of which is mounted on the propeller shaft. In the case of reversing the rotation of the propeller shaft, the bevel gear disposed on the drive shaft 180 rotates must be reversed in its normal direction.
Has been the practice to mount such bevel gears in the drive shaft in a manner that does not allow axial expansion or contraction of the drive shaft though the deflection of the same are compensated. In the present invention, the bevel gear is mounted on the propeller shaft via a spline connection and the housing is supported by suitable bearings.
BRIEF DESCRIPTION OF THE DRAWINGS
Having thus generally described the nature of the invention, reference is now made to the accompanying drawings, showing by way of illustration a preferred embodiment thereof, and in which:
. Figure 1 is an axial view taken through the planetary gear transmission of the second stage for converting the reverse rotation;
. Figure 2 is a schematic view of the planetary gears of the first stage slightly taken along line 2 - 2 of FIG. 1;
. Figure 3 is a schematic view of the planetary gears of the second stage somewhat taken along line 4 - 4 in Fig. 1 but showing the planetary gears rotatably disposed standard;
. Figure 4 is a somewhat schematic view along line 4 - 4 in Fig. 1, showing the gears in the arrangement of FIG. 1 for reverse rotation;
. Figure 5 is a fragmentary axial cross section of a further detail of the present invention;
. Figure 6 is a fragmentary view similar to FIG. 5 showing the state of the art;
. 7 is a fragmentary axial cross section of a detail of another embodiment of the present invention, and
. Figure 8 is a fragmentary schematic view of the planetary gear along line 2 - 2 of FIG. 1 showing the first stage in a reverse rotation.
Description of the Preferred Embodiments
Referring now to the drawings and especially to FIG. 1, there is shown the gear box of a gas turbine engine adapted to drive a propeller. The planetary gear assembly 10 which forms the gear box includes a housing assembly 12 formed by brackets 14 and 16 are held together along the flanges 18 and 20 by bolts 22. A ring gear 24 extends around the cavity formed by the housing assembly 12 and includes a flange 26 which is securely held between the flanges 18 and 20 of the shells 14 and 16 by bolts 22. The ring gear 24 has a first stage portion 28 with helical grooves and a second portion of the stage 30 with the gear teeth. An output shaft 32 of the gas turbine engine 1 is shown schematically at one end thereof and a propeller shaft 34 is illustrated at the other end of the housing.
A planetary gear 36 is coupled to the output shaft 32. The sun gear includes a cylindrical extension 38, as shown in Fig. 1. A first integrated carrier phase 40 is provided in the first stage, and includes a cylindrical extension 42 mounted in housing 16 by bearings 43. The first stage carrier 40 includes a pair of hubs 44 and 48. Within the hub 44 is provided an oil passage 46 to lead lubricating oil to the gears, as will be described.
In the first stage, as shown in Fig. 2, three gears 64 mounted on a support 40.
The gear 64 is mounted in the following manner: A sprocket bolt 50 extends between the hubs 44 and 48 and presses as cylindrical magazine 60. A bolt 70 secures the magazine 60 to the hubs 44 and 48 and also coupled to the caps 52 and 54, respectively. Is the bolt head 58 and nut 56 press against the end caps 54 and 52 which in turn is compressed axially in the stud 60. This magazine 60 is slightly longer than the width of the centers 44 and 48. Therefore, the hubs 44 and 48 are not pre-loaded. Each gear 64 is mounted in a journal 60 and a bearing metal bearing 62 is provided to allow the gear 64 to rotate with minimal friction in the journal 60. Lubrication passageway 46 enter the space formed by the cylindrical magazine 60 and caps 52 and 54 and passes through the filters 68 through conduits 66 in the magazine 60 in the area of bearing metal.
Each of the three gears 64 having gear teeth 72 which mesh with the sun gear 36 and ring gear 74. The ring gear 74 is helically grooved portion of the ring gear 28 in order to allow the ring gear 74 to have axial movement, so that as the load increases or decreases, which in turn reacts in the Hydraulic diaphragm 65.
A splined coupling 76 is provided in the center of the first stage and extends into the second stage area. The coupling spline 76 includes a spline coupling segment 78 of the hub extension 48 of the holder 40.
A sun gear 82 is provided in the second stage with internal spline 83 engaged by the gear segment 80 of the coupling 76.
The second stage is shown in Fig. 1 provides for reverse rotation. Therefore, the gears 94 are provided with gears 96 and 94 engage the ring gear portion 30, on one hand, and meshing with gears 96, on the other side. The planetary gears 96 engage the sun gear 82.
The carrier 86 in the second stage of assembly is shown so the combination of gears for reverse rotation. The gears are mounted on the holder 86 in a manner identical to the assembly described with respect to the gears 64 and carrier 40. The carrier 86 includes hubs 88 and 90 over 92.
Gear 96, shown in Fig. 1 is identified with identical numbers to numbers used with respect to the gear 64, but raised by 100. As shown, both carriers 86 and 40 are cantilever type carriers, and the carrier 86 has a splined extension 87 to the propeller shaft 34.
. Figure 3 illustrates the second stage of rotation setting standard comprises five gears 96a to 30 mesh and the crown gear 82. Therefore, in the standard rotation, a sun gear 36 rotates the planetary gears 64 against the stationary ring gear 74, causing the carrier 40 to rotate in the same direction as the sun gear.
Coupling toothing 76 transfers this rotation of sun gear 82. If the second stage is composed of gears 96a, as shown in Fig. 3, below, similarly sun gear 82 rotates the gears 96a against the ring gear 30, causing the bracket 86 to rotate in the same direction as the sun gear 84 and the output shaft 32. If however, reverse rotation is required, the second stage carrier 86 is replaced by a carrier 86 having a combination of gears illustrated by the gears 94 and 96. The gears 94 and 96 are selected such that are reasonably equivalent to the weight of gears 96a from ten gear must be provided in a reverse configuration instead of the five gears in the standard configuration of rotation of the figure. Three. Moreover, the gears are selected so that the transmission ratio is the same whether it is the standard configuration of rotation of the figure. 3 to the configuration of the reverse rotation of the figure. April. The carriers 86 are identical, except that the machining is different in the region of the gears. Therefore, one physically the same for the reverse rotation, except for the additional machining required because the added amount of gearing.
In the case of reverse rotation the configuration as shown in FIGS. 1 and 4, the sun gear 82 rotates gear 96 which in turn rotates gear 94 in the reverse direction against the sun gear 36 and the resulting rotation is reversed such that the carrier 86 rotates in a reverse direction from the sun gear 82 and the output shaft 32. Since the carrier 86 is connected in a spline to the propeller shaft 34, the shaft 34 will rotate in the same direction as the carrier 86 which is opposite to the rotation axis 32.
Two-stage transmission is shown in Fig. 1 significantly reduces the rotation thereof for high torque. For example, where the output shaft of the gas turbine may spin at 30,000 rpm, the propeller shaft 34, given the configuration shown in this application, to rotate at about 1600 rpm
In operation, it is noted that although the second stage has been described in terms of normal or reverse rotation, it may be that the first phase is used for providing reverse rotation. It would actually be even easier to use from the first stage of the first stage in this case has only three gears and therefore the reverse configuration would fixed gears. . Figure 8 shows the planetary gears arranged to reverse rotation of the first stage. Therefore, the gears 65 and 67 replace gear 64 in this case.
In any case, when switching the rotation of a motor in particular, pins 22 are removed to thereby separate the housing 14 of the housing 16. The ring gear 24 can be easily removed from the first stage, due to the splined connection between the ring gear 74 and the ring gear segment 28. The carrier 86 or 40, as the case may be, are then replaced by one with standard or reverse configuration.
As shown in the figure. 5, there is an attachment shaft 228 which is driven by the propeller shaft 34. If given the configuration of rotation to the shaft 34, the drive shaft should be amended 228 accessory. Therefore, the bevel gear 222 which is mounted in a bearing 214 via bearings 212 on the housing assembly 210, must be removed and turned 180 which is mounted in bearing 214 in the case of the present invention is driven by a toothed ring 216 mounted on the shaft 34 via the lock nut 218 which is threaded into the threads 220. The toothed ring 216 must also be changed in the case of reverse rotation. A toothed ring 216 is provided with grooves 224 which engages with the bevel gear 222. The bevel gear 222 has teeth 226 which mesh with teeth 234 on the crown gear 230 fixed to shaft 228 through the cylindrical extension 232 and bearing sleeve articulated 233.
An advantage of this configuration is that the bevel gear 222 is mounted on the housing and on the shaft 34 as has been done previously, as shown in Fig. 6 showing the prior art. In this case, the bevel gear 250, as shown, is mounted directly on the shaft 34. Any axial expansion or retraction of the shaft causes the bevel gear 250 to join or loosen against the sprocket 254. In the present invention, the grooves 224 allow for the axial clearance in relation to the bevel gear 222.
. Figure 7 of the drawings shows another embodiment of the gears 94 and 96. Empirically, it has been determined that the ratio of length to diameter of a gear should not exceed 0860. This relationship takes into account the deviation, the contact teeth, reliability, durability, etc. To overcome this engagement and to comply with the relation mentioned above, the gears 96 and 94 may be bent, as shown in Figure . 7, for example, the gears 294a and 294b that can be, but not necessarily, separated by a spacer 295. Since the gear cylinder is mounted on the magazine 60 in the case of FIG. 1 and 260 in the case of FIG. 7, the rest of the gear assembly does not change even though the cylinder gear itself can be duplicated.
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