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EP-4741647-A1 - ENGINE ACCESSORY MOUNTING ASSEMBLY

EP4741647A1EP 4741647 A1EP4741647 A1EP 4741647A1EP-4741647-A1

Abstract

A mounting arrangement includes a casing (17) of an aircraft engine (10) extending around an axis (11), an accessory (22), and a bracket (40) for mounting the accessory to the casing (17). The bracket (40) includes a first bracket segment (44') coupled to the casing (17) at a first mounting point, a second bracket segment (48') coupled to the accessory at a second mounting point, and a wire rope isolator (54') including a looped wire (56') coupling the first bracket segment (44') to the second bracket segment (48'). The first bracket segment (44') at the first mounting point and the second bracket segment (48') at the second mounting point extend in intersecting planes.

Inventors

  • DOWNARD, SEAN
  • FAZARI, EDWARD
  • SWITZER, WILLIAM

Assignees

  • Pratt & Whitney Canada Corp.

Dates

Publication Date
20260513
Application Date
20251107

Claims (12)

  1. A mounting arrangement, comprising: a casing (17) of an aircraft engine (10) extending around an axis (11); an accessory (22); and a bracket (40') for mounting the accessory (22) to the casing (17), the bracket (40') comprising: a first bracket segment (44') coupled to the casing (17) at a first mounting point; a second bracket segment (48') coupled to the accessory (22) at a second mounting point; and a wire rope isolator (54') including a looped wire (56') coupling the first bracket segment (44') to the second bracket segment (48'), wherein the first bracket segment (44') at the first mounting point and the second bracket segment (48') at the second mounting point extend in intersecting planes.
  2. The mounting arrangement as defined in claim 1, wherein: the first bracket segment (44') includes a planar section (44a') coupled to a flange (46) of the casing (17) at the first mounting point, and an angled section (44b') extending from the planar section (44a') and coupled to the looped wire (56'); the second bracket segment (48') includes a planar section (48a') coupled to a flange (34a) of the accessory (22) at the second mounting point, and an angled section (48b') extending from the planar section (48a') and coupled to the looped wire (56'); and the first and second mounting points are axially and radially spaced-part from one another relative to the axis (11).
  3. The mounting arrangement as defined in claim 2, wherein the planar section (44a') of the first bracket segment (44') and the planar section (48a') of the second bracket segment (48') extend in directions normal to one another.
  4. The mounting arrangement as defined in claim 2 or 3, wherein the angled section (44b') of the first bracket segment (44') and the angled section (48b') of the second bracket segment (48') each include a plurality of apertures (44c'; 48c') through which the looped wire (56') extends.
  5. The mounting arrangement as defined in claim 4, wherein the apertures (44c'; 48c') are distributed substantially across an entire width of the first bracket segment (44') and the second bracket segment (48').
  6. The mounting arrangement as defined in any of claims 2 to 5, wherein the angled section (44b') of the first bracket segment (44') and the angled section (48b') of the second bracket segment (48') are coupled to the looped wire (56') at diametrically opposed locations along the looped wire (56').
  7. The mounting arrangement as defined in any preceding claim, wherein the accessory (22) is a cooling manifold (22), and the wire rope isolator (54') has characteristics including: a wire diameter, a wire length, a degree of wire twist, and a number of individual wires braided together, the characteristics of the wire rope isolator (54') are selected to dampen vibrations from the casing (17) of the aircraft engine (10) to the cooling manifold (22).
  8. The mounting arrangement as defined in any preceding claim, wherein the looped wire (56') extends substantially across an entire width of the first bracket segment (44') and the second bracket segment (48').
  9. A method for absorbing vibrations between an accessory (22) and a casing (17) of an aircraft engine (10), comprising: coupling the accessory (22) to the casing (17) via brackets (40'), at least one of the brackets (40') having a first bracket segment (44') coupled to the casing (17), a second bracket segment (48') coupled to the accessory, and a wire rope isolator (54') including a looped wire (56') coupling the first bracket segment (44') to the second bracket segment (48'), the looped wire (56') dampening vibrations between the accessory and the casing (17).
  10. The method as defined in claim 9, wherein coupling the accessory (22) to the casing (17) via brackets (40') includes coupling the looped wire (56') to the first bracket segment (44') and to the second bracket segment (48') via apertures (44c'; 48c') distributed substantially across the first bracket segment (44') and the second bracket segment (48').
  11. The method as defined in claim 10, wherein coupling the looped wire (56') to the first bracket segment (44') and to the second bracket segment (48') includes coupling the looped wire (56') to the first bracket segment (44') and to the second bracket segment (48') across an entire width of the first bracket segment (44') and the second bracket segment (48').
  12. The method as defined in claim 9, 10 or 11, wherein coupling the accessory (22) to the casing (17) via brackets (40') includes securing the first bracket segment (44') to the casing (17) in a planar direction normal to a planar direction of the second bracket segment (48') secured to the accessory (22).

Description

TECHNICAL FIELD The invention relates generally to aircraft engines, and, more particularly, to mounting arrangements in aircraft engines. BACKGROUND Aircraft engines may include various accessories, such as accessory gearboxes, fluid tanks and cooling manifolds. These accessories are mounted to the engine casing, for instance, via mounting arrangements comprising one or more brackets. These brackets are subjected to various dynamic and thermal loads, which may cause premature wear. Improvements are desired. SUMMARY In one aspect of the invention, there is provided a mounting arrangement, comprising: a casing of an aircraft engine extending around an axis; an accessory; a bracket for mounting the accessory to the casing, the bracket comprising a first bracket segment coupled to the casing at a first mounting point (e.g., defined by the casing); a second bracket segment coupled to the accessory at a second mounting point (e.g., defined by the accessory); and a wire rope isolator including a looped wire coupling the first bracket segment to the second bracket segment, the first bracket segment at the first mounting point and the second bracket segment at the second mounting point extending in intersecting planes (e.g., a portion of the first bracket segment at the first mounting point extends along a plane which intersects with a plane along which a portion of the second bracket segment at the second mounting point extends and/or a portion of the accessory at or defining the second mounting point extends along a plane which intersects with a plane along which a portion of the casing at or defining the first mounting point extends). The mounting arrangement described above may include any of the following features, in any combinations. In any of the aspects or embodiments described above or herein, the first bracket segment may include a planar section coupled (e.g., attached, bonded or connected) to a flange of the casing at the first mounting point, and an angled section (e.g., at an angle to a plane of the planar section) extending from the planar section and coupled to (e.g., attached, bonded, connected, in contact with or captured by) the looped wire. The second bracket segment may include a planar section coupled (e.g., attached, bonded or connected) to a flange of the accessory at the second mounting point, and an angled section (e.g., at an angle to a plane of the planar section) extending from the planar section and coupled to (e.g., attached, bonded, connected, in contact with or captured by) the looped wire. The first and second mounting points may be axially and radially spaced-part from one another relative to the axis. In any of the aspects or embodiments described above or herein, the planar section of the first bracket segment and the planar section of the second bracket segment may extend in directions normal to one another. For example, a plane of the planar section of the first bracket segment and a plane of the planar section of the second bracket segment may be perpendicular to one another. In any of the aspects or embodiments described above or herein, the angled section of the first bracket and the angled section of the second bracket may each include a plurality of apertures through which the looped wire extends. In any of the aspects or embodiments described above or herein, the apertures may be distributed substantially across a (respective) entire width of each of the first bracket segment and the second bracket segment. In any of the aspects or embodiments described above or herein, the accessory may be a cooling manifold. In any of the aspects or embodiments described above or herein, the wire rope isolator may have characteristics including: a wire diameter, a wire length, a degree of wire twist, and a number of individual wires braided together. The characteristics of the wire rope isolator may be selected to dampen vibrations from the casing of the aircraft engine to the accessory (e.g., the cooling manifold). In any of the aspects or embodiments described above or herein, the angled section of the first bracket and the angled section of the second bracket are coupled to (e.g., attached, bonded, connected, in contact with or captured by) the looped wire at diametrically opposed locations along the looped wire. For example, the looped wire may comprise a plurality of loops, rings or turns which may each be coupled to the angled section of the first bracket and the angled section of the second bracket at diametrically opposed locations of each loop, ring or turn. In any of the aspects or embodiments described above or herein, the looped wire may comprise a plurality of loops, rings or turns. In any of the aspects or embodiments described above or herein, the looped wire may comprise or otherwise be formed into a helical shape. In any of the aspects or embodiments described above or herein, the accessory may comprise a cooling manifold. In any of the aspects or embodiments describe