Aircraft engine with exhaust having removable deflector

Patent metadata

Field	Value
Publication number	US-12420941-B2
Application number	US-202218060659-A
Country	US
Kind code	B2
Filing date	Dec 1, 2022
Priority date	Dec 1, 2022
Publication date	Sep 23, 2025
Grant date	Sep 23, 2025

Abstract

An aircraft engine, comprising a thermal engine, an axial turbine having a turbine inlet, and an exhaust assembly fluidly connecting the thermal engine to the axial turbine. The exhaust assembly includes a housing and a deflector removably mounted within the housing. The deflector has circumferentially distributed vanes. The deflector is a first deflector, having a first set of geometric characteristics, that is removable from the housing and replaceable by a second deflector having a second set of geometric characteristics different from the first set of geometric characteristics. The first deflector is one of a first class of deflectors and the second deflector is one of a second class of deflectors, the first and second class of deflectors respectively defining first and second exhaust flow profiles that differ from each other.

First claim

The invention claimed is:

1. An aircraft engine, comprising:
a thermal engine having an engine inlet and an engine outlet;
an axial turbine having a turbine inlet; and
an exhaust assembly fluidly connecting the engine outlet of the thermal engine to the turbine inlet of the axial turbine, the exhaust assembly having a exhaust inlet fluidly connected to the engine outlet and an exhaust outlet fluidly connected to the turbine inlet, the exhaust assembly including:
a housing extending circumferentially about a central axis, the housing having an outer wall and an inner wall disposed radially inwardly of the outer wall relative to the central axis, the inner wall and the outer wall curving from a radial orientation at the exhaust inlet to an axial orientation at the exhaust outlet, the exhaust outlet being annular and defined radially between the inner wall and the outer wall; and
a deflector removably mounted within the housing, the deflector having vanes circumferentially distributed about the central axis, flow passages interspaced between the vanes, the flow passages curving from passages inlets to passage outlets, axial components of passage axes of the flow passages increasing from the passage inlets to the passage outlets,

wherein the deflector is a first deflector having a first set of geometric characteristics, the deflector removable from the housing and replaceable by a second deflector having a second set of geometric characteristics different from the first set of geometric characteristics, wherein the first deflector is one of a first class of deflectors and the second deflector is one of a second class of deflectors, the first and second class of deflectors respectively defining first and second exhaust flow profiles that differ from each other.

2. The aircraft engine of claim 1 , wherein the first flow profile is defined by a first flow area defined between first trailing edges of circumferentially adjacent vanes of the first deflector, the second flow profile is defined by a second flow area defined between second trailing edges of circumferentially adjacent vanes of the second deflector, the first flow area different than the second flow area.

3. The aircraft engine of claim 1 , wherein the housing includes a first housing section and a second housing section detachably secured to the first housing section.

4. The aircraft engine of claim 1 , wherein the deflector includes a first shroud and a second shroud, the vanes extending from the first shroud to the second shroud, the deflector removably mounted to the housing via one or more of the first shroud and the second shroud.

5. The aircraft engine of claim 4 , wherein the deflector is mounted to the housing via the one or more of the first shroud and the second shroud via pins circumferentially distributed about the central axis, the pins securing the first shroud to the housing.

6. The aircraft engine of claim 4 , comprising dampers disposed between the first shroud and the housing and between the second shroud and the housing.

7. The aircraft engine of claim 6 , wherein the dampers are rope seals annularly extending around the central axis.

8. The aircraft engine of claim 1 , wherein the thermal engine has an engine shaft drivingly engaged to a rotatable load, the axial turbine drivingly engaged to the engine shaft to compound power with the thermal engine.

9. The aircraft engine of claim 8 , comprising a compressor in driving engagement with the axial turbine, the compressor having a compressor inlet receiving ambient air and a compressor outlet fluidly connected to the engine inlet.

10. The aircraft engine of claim 9 , wherein the axial turbine is devoid of a stator between the exhaust outlet and an upstream-most rotor of the axial turbine.

11. The aircraft engine of claim 10 , wherein the housing includes a shroud wall that extends axially downstream towards the axial turbine, and a radial tip clearance gap is defined between radially outer tips of the upstream-most rotor of the axial turbine and a radially inwardly facing surface the shroud wall of the housing.

12. An exhaust assembly for interconnecting a thermal engine to an axial turbine, comprising:
a housing extending circumferentially about a central axis and having an inlet extending tangentially relative to a circumference of the housing and an outlet extending circumferentially about the central axis and oriented axially relative to the central axis, the housing including a first housing section and a second housing section detachably secured to the first housing section, the first and second housing sections defining a deflector-receiving cavity between the first and second housing sections, the housing having an outer wall and an inner wall disposed radially inwardly of the outer wall relative to the central axis, the inner wall and the outer wall curving from a radial orientation at the inlet to an axial orientation at the outlet, the outlet being annular and defined radially between the inner wall and the outer wall; and
a deflector removably mounted within the deflector-receiving cavity, the deflector having vanes circumferentially distributed about the central axis, flow passages interspaced between the vanes, the flow passages curving from passages inlets to passage outlets.

13. The exhaust assembly of claim 12 , wherein a cross-sectional area of the housing at the inlet of the housing is square or rectangular.

14. The exhaust assembly of claim 12 , wherein axial components of the flow passages increase in a direction from the passage inlets toward the passage outlets.

15. The exhaust assembly of claim 12 , wherein the deflector includes a first shroud and a second shroud, the vanes extending from the first shroud to the second shroud, the deflector removably mounted to the housing via one or more of the first shroud and the second shroud.

16. The exhaust assembly of claim 15 , comprising dampers disposed between the first shroud and the housing and between the second shroud and the housing.

Assignees

• Pratt & Whitney Canada

Inventors

• Lefebvre Guy
• Gover Christopher

Classifications

• F02B41/10

  in exhaust turbines (use of exhaust turbines for charging F02B37/00) · CPC title

• F02C6/12

  Turbochargers, i.e. plants for augmenting mechanical power output of internal-combustion piston engines by increase of charge pressure · CPC title

• F05D2260/96

  Preventing, counteracting or reducing vibration or noise · CPC title

• F01N13/08

  Other arrangements or adaptations of exhaust conduits {(pipes, joints or supports therefor in general F16L; collecting or removing exhaust gases of vehicle engines in workshops B08B15/00, on highways E01C1/005)} · CPC title

• F01D9/048

  for radial admission · CPC title