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EP-4741631-A2 - ROTOR ASSEMBLY FOR A ROTARY ENGINE

EP4741631A2EP 4741631 A2EP4741631 A2EP 4741631A2EP-4741631-A2

Abstract

A rotor housing (46) for an aircraft rotary engine (12) includes a side housing body (82) and a rail (84). The side housing body (82) extends along an axis between and to an inner side (94) and an outer side (96). The side housing body (82) forms a fluid cooling passage (106) and a plurality of ribs (114). The fluid cooling passage (106) extends about the axis at the inner side (94). The plurality of ribs (114) are coincident with and extend into the fluid cooling passage (106). The plurality of ribs (114) are distributed about the fluid cooling passage (106) as an array of ribs (114). The rail (84) is disposed at the plurality of ribs (114). The rail (84) extends about the fluid cooling passage (106). The side housing body (82) and the rail (84) form a plurality of fluid cooling channels (118) connected in fluid communication with the fluid cooling passage (106).

Inventors

  • BARBERGER, JEREMIE
  • BOUSQUET, MICHEL

Assignees

  • Pratt & Whitney Canada Corp.

Dates

Publication Date
20260513
Application Date
20240408

Claims (15)

  1. A rotor housing (46) for an aircraft rotary engine (12), the rotor housing (46) comprising: a rotor housing body (52) disposed about an axis, the rotor housing body (52) extending between and to a first axial end (56) and a second axial end (58); a side housing body (82) disposed at the first axial end (56), the side housing body (82) forming a first fluid cooling passage (106) and a plurality of ribs (114), the first fluid cooling passage (106) extending about the axis, the plurality of ribs (114) coincident with and extending into the first fluid cooling passage (106), the plurality of ribs (114) distributed about the fluid cooling passage (106) as an array of ribs (114); a rail (84) disposed at the plurality of ribs (114), the rail (84) extending about the fluid cooling passage (106); and a side plate (80) positioned between and contacting the rail (84) and the rotor housing body (52).
  2. The rotor housing (46) of claim 1, wherein the rotor housing body (52) forms a second fluid cooling passage (136) connected in fluid communication with the first fluid cooling passage (106).
  3. The rotor housing (46) of claim 2, wherein the side housing body (82) and the rail (84) form a plurality of fluid cooling channels (118) connected in fluid communication with the first fluid cooling passage (106).
  4. The rotor housing (46) of claim 3, wherein the plurality of fluid cooling channels (118) connect the second fluid cooling passage (136) in fluid communication with the first fluid cooling passage (106).
  5. The rotor housing (46) of claim 3 or 4, wherein each fluid cooling channel (118) of the plurality of fluid cooling channels (118) is formed by adjacent ribs (114) of the plurality of ribs (114).
  6. A rotor housing (46) for an aircraft rotary engine (12), the rotor housing (46) comprising: a side housing body (82) extending along an axis (28) between and to an inner side (94) and an outer side (96), the side housing body (82) forming a fluid cooling passage (106) and a plurality of ribs (114), the fluid cooling passage (106) extending about the axis at the inner side (94), the plurality of ribs (114) coincident with and extending into the fluid cooling passage (106), the plurality of ribs (114) distributed about the fluid cooling passage (106) as an array of ribs (114); and a rail (84) disposed at the plurality of ribs (114), the rail (84) extending about the fluid cooling passage (106); the side housing body (82) and the rail (84) forming a plurality of fluid cooling channels (118) connected in fluid communication with the fluid cooling passage (106).
  7. The rotor housing (46) of claim 6, wherein each fluid cooling channel (118) of the plurality of fluid cooling channels (118) includes a channel inlet (120) and the channel inlet (120) is disposed at the fluid cooling passage (106).
  8. The rotor housing (46) of claim 6 or 7, wherein each fluid cooling channel (118) of the plurality of fluid cooling channels (118) includes a channel outlet (122) and the channel outlet (122) is disposed at the inner side (94).
  9. The rotor housing (46) of claim 6, 7 or 8, wherein each fluid cooling channel (118) of the plurality of fluid cooling channels (118) is formed by adjacent ribs (114) of the plurality of ribs (114).
  10. The rotor housing (46) of any of claims 6 to 9, wherein the side housing body (82) forms an outer radial side (108), an inner radial side (110), and an outer axial side (112) of the fluid cooling passage (106), the outer radial side (108) and the inner radial side (110) extending between and to the inner side (94) and the outer axial side (112), wherein, optionally, each rib (114) of the plurality of ribs (114) extends from the outer radial side (108) into the fluid cooling passage (106).
  11. The rotor housing (46) of any of claims 6 to 10, wherein the rail (84) includes an axially-extending portion (124) and a radially-extending portion (126), the axially-extending portion (124) extending from the radially-extending portion (126) to the inner side (94), wherein, optionally, the radially-extending portion (126) extends from the axially-extending portion (124) to a distal end (116) of each rib (114) of the plurality of ribs (114).
  12. A rotary engine assembly (10) for an aircraft, the rotary engine assembly (10) comprising: a rotatable engine shaft (26) extending along a rotational axis (28); a rotor (48) coupled to an eccentric portion (68) of the rotatable engine shaft (26); and a rotor housing (46) surrounding and forming a rotor cavity (60) for the rotor (48), the rotor housing (46) including: a side housing body (82) forming a fluid cooling passage (106) and a plurality of ribs (114), the fluid cooling passage (106) extending about the rotational axis (28), the plurality of ribs (114) coincident with and extending into the fluid cooling passage (106); a rail (84) disposed at the plurality of ribs (114), the rail (84) extending about the fluid cooling passage (106); and a side plate (80) including an inner side (86), an outer side (88), and a perimeter edge (90), the perimeter edge (90) disposed at the rail (84), the inner side (86) forming a portion of the rotor cavity (60).
  13. The rotary engine assembly (10) of claim 12, wherein: the rotatable engine shaft (26) extends through the side housing body (82) and the side plate (80) along the rotational axis (28); and/or the rotor housing (46) further includes a seal (138, 140) disposed between the rail (84) and the side plate (80).
  14. The rotary engine assembly (10) of claim 12 or 13, wherein the outer side (88) further forms the fluid cooling passage (106).
  15. The rotary engine assembly (10) of claim 12, 13 or 14, wherein: the side housing body (82) and the rail (84) form a plurality of fluid cooling channels (118) connected in fluid communication with the fluid cooling passage (106), and, optionally, the side housing body (82) and the rail (84) form a channel inlet (120) and a channel outlet (122) for each fluid cooling channel (118) of the plurality of fluid cooling channels (118); and/or the rail (84) includes an axially-extending portion (124) and a radially-extending portion (126), the perimeter edge (90) disposed at the axially-extending portion (124) and the outer side (88) disposed at the radially-extending portion (126).

Description

TECHNICAL FIELD This disclosure relates generally to rotary engines for aircraft and, more particularly, to a rotor housing for a rotary engine. BACKGROUND OF THE ART A rotary engine for an aircraft may be configured, for example, as a Wankel engine. The rotary engine includes one or more rotors configured to eccentrically rotate within a rotor housing. Various rotor housing configurations are known for rotary engines. While these known rotor housings have various advantages, there is still room in the art for improvement. SUMMARY It should be understood that any or all of the features or embodiments described herein can be used or combined in any combination with each and every other feature or embodiment described herein unless expressly noted otherwise. According to an aspect of the present disclosure, a rotor housing for an aircraft rotary engine includes a side housing body and a rail. The side housing body extends along an axis between and to an inner side and an outer side. The side housing body forms a fluid cooling passage and a plurality of ribs. The fluid cooling passage extends about the axis at the inner side. The plurality of ribs are coincident with and extend into the fluid cooling passage. The plurality of ribs are distributed about the fluid cooling passage as an array of ribs. The rail is disposed at the plurality of ribs. The rail extends about the fluid cooling passage. The side housing body and the rail form a plurality of fluid cooling channels connected in fluid communication with the fluid cooling passage. In any of the aspects or embodiments described above and herein, each fluid cooling channel of the plurality of fluid cooling channels may include a channel inlet and the channel inlet may be disposed at the fluid cooling passage. In any of the aspects or embodiments described above and herein, each fluid cooling channel of the plurality of fluid cooling channels may include a channel outlet and the channel outlet may be disposed at the inner side. In any of the aspects or embodiments described above and herein, each fluid cooling channel of the plurality of fluid cooling channels may be formed by adjacent ribs of the plurality of ribs. In any of the aspects or embodiments described above and herein, the side housing body may form an outer radial side, an inner radial side, and an outer axial side of the fluid cooling passage. The outer radial side and the inner radial side may extend between and to the inner side and the outer axial side. In any of the aspects or embodiments described above and herein, each rib of the plurality of ribs may extend from the outer radial side into the fluid cooling passage. In any of the aspects or embodiments described above and herein, the rail may include an axially-extending portion and a radially-extending portion. The axially-extending portion may extend from the radially-extending portion to the inner side. In any of the aspects or embodiments described above and herein, the radially-extending portion may extend from the axially-extending portion to a distal end of each rib of the plurality of ribs. According to another aspect of the present disclosure, a rotary engine assembly for an aircraft includes a rotatable engine shaft extending along a rotational axis, a rotor coupled to an eccentric portion of the rotatable engine shaft, and a rotor housing. The rotor housing surrounds and forms a rotor cavity for the rotor. The rotor housing includes a side housing body, a rail, and a side plate. The side housing body forms a fluid cooling passage and a plurality of ribs. The fluid cooling passage extending about the rotational axis. The plurality of ribs are coincident with and extend into the fluid cooling passage The rail is disposed at the plurality of ribs. The rail extends about the fluid cooling passage. The side plate includes an inner side, an outer side, and a perimeter edge. The perimeter edge is disposed at the rail. The inner side forms a portion of the rotor cavity. In any of the aspects or embodiments described above and herein, the rotatable engine shaft may extend through the side housing body and the side plate along the rotational axis. In any of the aspects or embodiments described above and herein, the rotor housing may further include a seal disposed between the rail and the side plate. In any of the aspects or embodiments described above and herein, the outer side may further form the fluid cooling passage. In any of the aspects or embodiments described above and herein, the side housing body and the rail may form a plurality of fluid cooling channels connected in fluid communication with the fluid cooling passage. In any of the aspects or embodiments described above and herein, the side housing body and the rail may form a channel inlet and a channel outlet for each fluid cooling channel of the plurality of fluid cooling channels. In any of the aspects or embodiments described above and herein, the rail may include an axiall