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EP-4471395-B1 - DRIVE ASSEMBLY AND METHOD OF ASSEMBLY

EP4471395B1EP 4471395 B1EP4471395 B1EP 4471395B1EP-4471395-B1

Inventors

  • DUROCHER, ERIC SYLVAIN

Dates

Publication Date
20260513
Application Date
20240531

Claims (8)

  1. A drive assembly comprising: a torque shaft (148, 248) rotatable around a rotation axis (246), the torque shaft (148, 248) having a first end (150, 250) and a second end (152, 252) opposite the first end (150, 250) along the rotation axis (246), a first reference feature (92) at an intermediary location between the first end (150, 250) and the second end (152, 252), and a sun gear (172, 272) integrated to the torque shaft (148, 248) at the first end (150, 250); a reference tube (154, 254) having a fixed end (156) secured to the torque shaft (148, 248) adjacent the second end (152, 252), a free end (158) having a second reference feature (90) adjacent the first reference feature (92), the reference tube (154, 254) extending around the torque shaft (148, 248); a torque sensor (42) fixed relative to the rotation axis (246), the torque sensor (42) operable to measure a distance between the first reference feature (92) and the second reference feature (90); a source shaft (162, 262) rotatable around the rotation axis (246), the source shaft (162, 262) coupled to the second end (152, 252); a ring gear (70) fixed relative the rotation axis (246) and concentric to the rotation axis (246); a plurality of planetary gears (64) circumferentially distributed around the rotation axis (246), the plurality of planetary gears (64) engaged between the sun gear (172, 272) and the ring gear (70); and an output shaft (168) having a carriage (66) receiving the plurality of planetary gears (64) in an individually rotatable manner, the output shaft (168) rotatable with the carriage (66) and the plurality of planetary gears (64) as a whole around the rotation axis (246).
  2. The drive assembly of claim 1, wherein the reference tube (154, 254) has an internal diameter, the second end (152, 252) has a first external diameter, and the sun gear (172, 272) has a second external diameter, the internal diameter being between the first external diameter and the second external diameter.
  3. The drive assembly of claim 1 or 2, wherein the fixed end (156) is fixed to the torque shaft (148, 248) via a plurality of circumferentially distributed pins.
  4. The drive assembly of any preceding claim, further comprising a bearing assembly (274) supporting one of the torque shaft (148, 248) and the source shaft (162, 262) adjacent the second end (152, 252).
  5. The drive assembly of claim 4, wherein the torque shaft (148, 248) is hollow and delimits an oil passage (296) between the first end (150, 250) and the second end (152, 252), the oil passage (296) open at the first end (150, 250), further comprising at least one oil nozzle (294) operable to direct a jet of oil into the oil passage (296) via the first end (150, 250), and one or more oil conduits extending between the oil passage (296) and the bearing assembly (274), optionally wherein the at least one oil nozzle (294) is further operable to direct a jet of oil to the plurality of planetary gears (64).
  6. The drive assembly of any preceding claim, wherein the torque shaft (148, 248) has a male spline (82) at the second end (152, 252), the source shaft (162, 262) has a female spline (82), and the source shaft (162, 262) is coupled to the torque shaft (148, 248) via an engagement of the male spline (82) and the female spline (82).
  7. The drive assembly of any of claims 1 to 5, wherein the torque shaft (148, 248) has a female spline (82) at the second end (152, 252), the source shaft (162, 262) has a male spline (82), and the source shaft (162, 262) is coupled to the torque shaft (148, 248) via an engagement of the male spline (82) and the female spline (82), optionally wherein: the female spline (82) is formed in a cavity (286) defined axially into the source shaft (162, 262), the cavity (286) receiving the male spline (82), the source shaft (162, 262) having a male member (290) extending into the cavity (286) along the rotation axis (246), the torque shaft (148, 248) further comprising a radially-inwardly projecting flange leading to a central aperture, the central aperture receiving the male member (290), the male member (290) secured axially to the torque shaft (148, 248).
  8. The drive assembly of any preceding claim, further comprising an engine (160, 260) coupled to the source shaft (162, 262), and a propeller (112) coupled to the output shaft (168), optionally wherein the engine (160, 260) is an electric engine (160, 260).

Description

TECHNICAL FIELD The application relates generally to aircraft engines and, more particularly, to the measurement of the torque transferred between an engine and an output shaft. BACKGROUND OF THE ART Aircraft engines may require a torque measurement system integrated to the drive assembly to detect shaft torque, such as to provide feedback to a control system used for operating the engine. While existing systems were satisfactory to a certain degree, there always remains room for improvement. Indeed, various contextual elements may motivate aircraft component designers to adapt existing solutions to new contexts, or to find new solutions. Moreover, aircraft component designers evolve in a complex environment where many factors are to be accounted for, such as volume, weight, costs (both initial and maintenance-related), assembly considerations, reliability, etc. EP 3 686 606 B1 discloses a shaft monitoring system. US 2011/056309 A1 discloses a device for measuring the torque transmitted by a power shaft. US 10 677 670 B2 discloses a twisting torque sensor. US 10 975 717 B2 discloses a torque monitoring device for a gas turbine engine. SUMMARY In one aspect of the present invention, there is provided a torque measurement system according to claim 1. Also disclosed herein is a torque transfer assembly comprising: a torque shaft rotatable around a rotation axis, the torque shaft having a first end and a second end opposite the first end along the rotation axis, a first reference feature at an intermediary location between the first end and the second end, and a sun gear integrated to the torque shaft, at the first end, the second end has a first external diameter, and the sun gear having a second external diameter greater than the first external diameter; and a reference tube having a fixed end secured to the torque shaft adjacent the second end, a free end having a second reference feature adjacent the first reference feature, the reference tube extending around the torque shaft, the reference tube having an internal diameter, the internal diameter being between the first external diameter and the second external diameter. Also disclosed herein is a method of assembling a torque transfer assembly, the method comprising: engaging a second end of a torque shaft into a free end of a reference tube bearing a first reference feature, and sliding the reference tube towards a first end of the torque shaft opposite the second end, until the free end of the reference tube reaches an intermediary location of the torque shaft, the torque shaft having a sun gear at the first end and a second reference feature at the intermediary location; and securing a fixed end of the reference tube to the second end of the torque shaft, the fixed end of the reference tube opposite the free end. DESCRIPTION OF THE DRAWINGS Reference is now made to the accompanying figures in which: Fig. 1 is a schematic cross-sectional view of a gas turbine engine;Fig. 2 is a schematic cross-sectional view of an example of an aircraft powerplant installation;Fig. 3 is a cross-sectional view of a torque transfer assembly for use with an aircraft powerplant;Fig. 4 is a cross-sectional view of another torque transfer assembly;Fig. 5 is a cross-sectional view of a further torque transfer assembly;Fig. 6 presents an enlarged portion of Fig. 5 showing additional detail;Fig. 7 presents an example of reference features for measuring torque; andFig. 8 presents a flow chart of an example method of assembling a torque transfer assembly. DETAILED DESCRIPTION Fig. 1 illustrates an example of an aircraft engine, and more specifically a gas turbine engine 10 of a type preferably provided for use in subsonic flight, generally comprising in serial flow communication a fan 12 through which ambient air is propelled, a compressor section 14 for pressurizing the air, a combustor 16 in which the compressed air is mixed with fuel and ignited for generating an annular stream of hot combustion gases around the engine axis 11, and a turbine section 18 for extracting energy from the combustion gases. The compressor section 14, fan 12 and turbine section 18 have rotating components which can be mounted on one or more shafts. Bearings 20 are used to provide smooth relative rotation between a shaft and casing (non-rotating component), and/or between two shafts which rotate at different speeds. An oil lubrication system 22 including an oil pump 24, sometimes referred to as a main pump, and a network of conduits and nozzles 26, is provided to feed the bearings 20 with oil. Seals 28 are used to contain the oil. A scavenge system 30 having cavities 32, conduits 34, and one or more scavenge pumps 36, is used to recover the oil, which can be in the form of an oil foam at that stage, from the bearings 20. The oil pump 24 draws the oil from an oil reservoir 38. Air/oil separating devices (not shown) may be provided in the return line. The gas turbine engine 10 presented in Fig. 1 is a type