Patent Application
20250154906
This disclosure relates generally to a turbine engine and, more particularly, to an engine accessory system for the turbine engine.
A gas turbine engine may include multiple engine accessories such as a pump, a generator and a motor. These engine accessories are typically mechanically coupled to an internal rotating assembly of the gas turbine engine through an accessory gearbox. Various types and configurations of accessory gearboxes are known in the art. While these known accessory gearboxes have various benefits, there is still room in the art for improvement.
According to an aspect of the present disclosure, an assembly is provided for a turbine engine. This assembly includes an inner tower shaft, a layshaft, an outer tower shaft, an intermediate gear system, an inner gearbox and an outer gearbox. The inner tower shaft is rotatable about an inner shaft axis. The layshaft is rotatable about a layshaft axis. The layshaft is coupled to the inner tower shaft through an inner bevel gearing connection. The outer tower shaft is rotatable about an outer shaft axis. The outer tower shaft is coupled to the layshaft through an outer bevel gearing connection. The intermediate gear system is configured to transfer mechanical power from the inner tower shaft to the layshaft and the outer tower shaft. The intermediate gear system includes the inner bevel gearing connection and the outer bevel gearing connection. The inner gearbox is coupled to the intermediate gear system through the layshaft. The outer gearbox is coupled to the intermediate gear system through the outer tower shaft.
According to another aspect of the present disclosure, another assembly is provided for a turbine engine. This assembly includes an inner tower shaft, a layshaft, an outer tower shaft, a gear system, an inner gearbox and an outer gearbox. The inner tower shaft is rotatable about an inner shaft axis. The layshaft is rotatable about a layshaft axis. The layshaft is coupled to the inner tower shaft through a first gearing connection. The outer tower shaft is rotatable about an outer shaft axis. The outer tower shaft is coupled to the inner tower shaft through a second gearing connection. The gear system is configured to transfer mechanical power from the inner tower shaft to the layshaft and the outer tower shaft. The gear system includes the first gearing connection and the second gearing connection. The inner gearbox is coupled to the gear system through the layshaft. The outer gearbox is coupled to the gear system through the outer tower shaft.
According to still another aspect of the present disclosure, another assembly is provided for a turbine engine. This assembly includes an inner tower shaft, a layshaft, an outer tower shaft, an intermediate gear system, an inner gearbox and an outer gearbox. The inner tower shaft is rotatable about an inner shaft axis. The layshaft is rotatable about a layshaft axis. The outer tower shaft is rotatable about an outer shaft axis which is non-parallel with the inner shaft axis. The intermediate gear system is coupled to the inner tower shaft, the layshaft and the outer tower shaft. The intermediate gear system is configured to transfer mechanical power from the inner tower shaft to the layshaft and the outer tower shaft. The inner gearbox is coupled to the intermediate gear system through the layshaft. The outer gearbox is coupled to the intermediate gear system through the outer tower shaft.
The first gearing connection may be a first bevel gearing connection. In addition or alternatively, the second gearing connection may be a second bevel gearing connection.
The inner shaft axis, the layshaft axis and the outer shaft axis may be disposed in a common reference plane.
The inner shaft axis may be angularly offset from the layshaft axis by an inner shaft-layshaft offset angle. The outer shaft axis may be angularly offset from the layshaft axis by an outer shaft-layshaft offset angle. The outer shaft-layshaft offset angle may be different than the inner shaft-layshaft offset angle.
The gear system may include a first inner shaft gear, a second inner shaft gear, an outer shaft gear and a layshaft gear. The first inner shaft gear may be rotatably fixed to the inner tower shaft and meshed with the layshaft gear. The second inner shaft gear may be rotatably fixed to the inner tower shaft and meshed with the outer shaft gear. The outer shaft gear may be rotatably fixed to the outer tower shaft. The layshaft gear may be rotatably fixed to the layshaft.
A diameter of the first inner shaft gear may be different than a diameter of the second inner shaft gear.
The assembly may also include an engine rotating assembly and an inner gear system. The engine rotating assembly may include a turbine rotor. The engine rotating assembly may be rotatable about an engine axis. The inner gear system may be configured to transfer the mechanical power from the engine rotating assembly to the inner tower shaft to drive operation of the inner gearbox and the outer gearbox.
The assembly may also include a high pressure turbine section and a low pressure turbine section. The turbine rotor may be disposed in the high pressure turbine section.
At least two of the inner shaft axis, the layshaft axis, the outer shaft axis or the engine axis may be disposed in a common reference plane.
At least two of the inner shaft axis, the layshaft axis or the outer shaft axis may be disposed in a common reference plane.
The inner shaft axis may be angularly offset from the outer shaft axis by an inner shaft-outer shaft offset angle. The inner shaft-outer shaft offset angle may be an obtuse angle.
The inner shaft axis may be non-parallel with the outer shaft axis.
The inner shaft axis may be angularly offset from the layshaft axis by an inner shaft-layshaft offset angle. The inner shaft-layshaft offset angle may be equal to or greater than ninety degrees. In addition or alternatively, the outer shaft axis may be angularly offset from the layshaft axis by an outer shaft-layshaft offset angle. The outer shaft-layshaft offset angle may be equal to or greater than ninety degrees.
The inner shaft axis may be angularly offset from the layshaft axis by an inner shaft-layshaft offset angle. The outer shaft axis may be angularly offset from the layshaft axis by an outer shaft-layshaft offset angle. The outer shaft-layshaft offset angle may be equal to the inner shaft-layshaft offset angle.
The inner shaft axis may be angularly offset from the layshaft axis by an inner shaft-layshaft offset angle. The outer shaft axis may be angularly offset from the layshaft axis by an outer shaft-layshaft offset angle. The outer shaft-layshaft offset angle may be different than the inner shaft-layshaft offset angle.
The intermediate gear system may include an inner shaft bevel gear, an outer shaft bevel gear and a layshaft bevel gear arranged between and meshed with the inner shaft bevel gear and the outer shaft bevel gear. The inner shaft bevel gear may be rotatably fixed to the inner tower shaft. The outer shaft bevel gear may be rotatably fixed to the outer tower shaft. The layshaft bevel gear may be rotatably fixed to the layshaft.
The intermediate gear system may include an inner shaft bevel gear, an outer shaft bevel gear, a first layshaft bevel gear and a second layshaft bevel gear. The inner shaft bevel gear may be rotatably fixed to the inner tower shaft and meshed with the first layshaft bevel gear. The outer shaft bevel gear may be rotatably fixed to the outer tower shaft and meshed with the second layshaft bevel gear. The first layshaft bevel gear may be rotatably fixed to the layshaft. The second layshaft bevel gear may be rotatably fixed to the layshaft.
A diameter of the first layshaft bevel gear may be different than a diameter of the second layshaft bevel gear.
The assembly may also include an engine housing. The engine housing may include an inner case and an outer case. The inner gearbox may be mounted to the inner case. The outer gearbox may be mounted to the outer case.
The present disclosure may include any one or more of the individual features disclosed above and/or below alone or in any combination thereof.
The foregoing features and the operation of the invention will become more apparent in light of the following description and the accompanying drawings.
The engine sections 28-31B are arranged sequentially along the engine axis 22 within an engine housing 34. This engine housing 34 includes an inner case 36 (e.g., a core case) and an outer case 38 (e.g., a fan case). The inner case 36 may house one or more of the engine sections 29A-31B; e.g., a core 40 or gas generator of the turbine engine 20. The outer case 38 may house at least the fan section 28.
Each of the engine sections 28, 29A, 29B, 31A and 31B includes a respective bladed rotor 42-46. Each of these bladed rotors 42-46 includes a plurality of rotor blades arranged circumferentially around and connected to one or more respective rotor disks. The rotor blades, for example, may be formed integral with or mechanically fastened, welded, brazed and/or otherwise attached to the respective rotor disk(s).
The HPC rotor 44 is coupled to and rotatable with the HPT rotor 45. The HPC rotor 44 of
The engine shafts 48, 52 and 60 are rotatably supported by a plurality of bearings 62; e.g., rolling element and/or thrust bearings. Each of these bearings 62 is connected to the engine housing 34 by at least one stationary structure such as, for example, an annular support strut. With this arrangement, each of the engine rotating assemblies 50 and 54 and its members may be rotatable about the engine axis 22.
During operation, air enters the turbine engine 20 through the airflow inlet 24. This air is directed through the fan section 28 and into a core flowpath 64 and a bypass flowpath 66. The core flowpath 64 extends sequentially through the engine sections 29A-31B; e.g., the engine core 40. The air within the core flowpath 64 may be referred to as “core air”. The bypass flowpath 66 extends through a bypass duct and bypasses the engine core 40. The air within the bypass flowpath 66 may be referred to as “bypass air”.
The core air is compressed by the LPC rotor 43 and the HPC rotor 44, and is directed into a combustion chamber 68 of a combustor in the combustor section 30. Fuel is injected into the combustion chamber 68 and mixed with the compressed core air to provide a fuel-air mixture. This fuel-air mixture is ignited and combustion products thereof flow through and sequentially cause the HPT rotor 45 and the LPT rotor 46 to rotate. The rotation of the HPT rotor 45 and the LPT rotor 46 respectively drive rotation of the HPC rotor 44 and the LPC rotor 43 and, thus, compression of the air received from a core airflow inlet. The rotation of the LPT rotor 46 also drives rotation of the fan rotor 42. The rotation of the fan rotor 42 propels the bypass air through and out of the bypass flowpath 66. The propulsion of the bypass air may account for a majority of thrust generated by the turbine engine 20, e.g., more than seventy-five percent (75%) of engine thrust. The turbine engine 20 of the present disclosure, however, is not limited to the foregoing exemplary thrust ratio.
Referring to
Examples of the engine accessories 72 include, but are not limited to, one or more electric machines, one or more pumps, one or more auxiliary compressors, one or more power transfer units, or any other mechanically driven device(s) and/or mechanical drive device(s). Examples of the electric machine include, but are not limited to, an electric generator, an electric motor, and an electric motor-generator. Examples of the pump include, but are not limited to, a fuel pump, a lubricant pump, a coolant pump, a water pump, and a hydraulic pump. Examples of the auxiliary compressor include, but are not limited to, a shaft driven compressor and a pneumatic compressor. Examples of the power transfer unit include, but are not limited to, a device that mechanically ties multiple engine rotating assemblies (e.g., the high speed and the low speed rotating assemblies 50 and 54 of
The engine accessories 72 of
The power transfer system 74 includes an accessory system drivetrain and a plurality of accessory gearboxes 78 and 80. The accessory system drivetrain of
The inner tower shaft 82 extends longitudinally along an inner shaft axis 92 between and to a radial inner end 94 of the inner tower shaft 82 and a radial outer end 96 of the inner tower shaft 82. The inner shaft inner end 94 is disposed in a radial inner region 98 of the turbine engine 20 with an engine shaft 100 (e.g., the high speed shaft 48 of
The inner tower shaft 82 is rotatable about its inner shaft axis 92. This inner shaft axis 92 is angularly offset from the engine axis 22 by an included inner shaft-engine shaft offset angle 104. The inner shaft-engine shaft offset angle 104 of
Referring to
The outer tower shaft 86 extends longitudinally along an outer shaft axis 114 between and to a radial inner end 116 of the outer tower shaft 86 and a radial outer end 118 of the outer tower shaft 86. The outer shaft inner end 116 is disposed in the engine intermediate region 102. The outer shaft outer end 118 is disposed in an outer region 120 to a radial exterior of the turbine engine 20 with the outer gearbox 80. This outer region 120 is disposed radially outboard of the bypass flowpath 66 and the outer case 38; e.g., radially outboard of the engine housing 34. With this arrangement, the outer tower shaft 86 extends radially across the bypass flowpath 66 (e.g., through a bypass flowpath bifurcation) from the outer shaft inner end 116 in the engine intermediate region 102 to the outer shaft outer end 118 in the outer region 120.
The outer tower shaft 86 is rotatable about its outer shaft axis 114. This outer shaft axis 114 is angularly offset from the layshaft axis 106 by an included outer shaft-layshaft offset angle 122. The outer shaft-layshaft offset angle 122 of
While the axes 22, 92, 106 and 114 of
The inner gear system 88 is configured as or otherwise includes a transmission, a gearbox and/or any other type of gearing which operatively couples and transfers mechanical power between the engine rotating assembly 76 and the inner tower shaft 82. The inner gear system 88 of
The intermediate gear system 90 is configured as or otherwise includes a transmission, a gearbox and/or any other type of gearing which operatively couples and transfers mechanical power between the inner tower shaft 82, the layshaft 84 and/or the outer tower shaft 86. The intermediate gear system 90 of
The inner gearbox 78 is mounted (directly or indirectly) to the inner case 36; e.g., see
The outer gearbox 80 is mounted (directly or indirectly) to the outer case 38; e.g., see
The outer gearbox 80 of
By providing the multiple gearboxes 78 and 80, the engine accessories 72 are located at multiple different locations within the turbine engine 20. This may reduce space requirements for engine accessories in the engine intermediate region 102 as well as reduce space requirement for engine accessories outside the outer case 38. By reducing the space requirements in the engine intermediate region 102, there are less restraints on bypass flowpath trajectory and/or size within the turbine engine 20. By reducing the space requirement in the outer region 120, an overall size of a nacelle for the turbine engine 20 may be reduced. These reductions may facilitate provision of a higher efficiency bypass flowpath design and/or reduced drag along the nacelle.
In some embodiments, referring to
The inner shaft outer gear 130 and the first layshaft gear 134 may be provided with a common (the same) gear diameter and/or bevel angle where the inner shaft outer gear 130 and/or the first layshaft gear 134 are bevel gears. Similarly, the outer shaft gear 132 and the second layshaft gear 136 may be provided with a common gear diameter. However, the gear diameter of the gears 132 and 136 of
In some embodiments, referring to
The second inner shaft outer gear 138 is disposed longitudinally between the first inner shaft outer gear 130 and the inner shaft inner gear 128; however, the present disclosure is not limited to such an exemplary arrangement. With this arrangement, the inner shaft-layshaft offset angle 112 may be different than (or alternatively the same as) the outer shaft-layshaft offset angle 122. In addition, by providing a connection between the inner tower shaft 82 and the outer tower shaft 86, the inner tower shaft 82 may independently transfer the mechanical power to the layshaft 84 and the outer tower shaft 86.
The first inner shaft outer gear 130 and the layshaft gear 134 may be provided with a common (the same) gear diameter and/or bevel angle where the inner shaft outer gear 130 and/or the first layshaft gear 134 are bevel gears. Similarly, the second inner shaft outer gear 138 and the outer shaft gear 132 may be provided with a common gear diameter. However, the gear diameter of the gears 132 and 138 of
The accessory system 70 may be included in various turbine engines other than the one described above. The accessory system 70, for example, may be included in a geared turbine engine where a geartrain connects one or more shafts to one or more rotors in a fan section, a compressor section and/or any other engine section. Alternatively, the accessory system 70 may be included in a turbine engine configured without a geartrain; e.g., a direct drive turbine engine. The accessory system 70 may be included in a turbine engine with a single spool, with two spools (e.g., see
While various embodiments of the present disclosure have been described, it will be apparent to those of ordinary skill in the art that many more embodiments and implementations are possible within the scope of the disclosure. For example, the present disclosure as described herein includes several aspects and embodiments that include particular features. Although these features may be described individually, it is within the scope of the present disclosure that some or all of these features may be combined with any one of the aspects and remain within the scope of the disclosure. Accordingly, the present disclosure is not to be restricted except in light of the attached claims and their equivalents.
