Connecting assembly for cooling the turbine of a turbine engine

Patent metadata

Field	Value
Publication number	US-11293303-B2
Application number	US-201715804738-A
Country	US
Kind code	B2
Filing date	Nov 6, 2017
Priority date	Nov 8, 2016
Publication date	Apr 5, 2022
Grant date	Apr 5, 2022

Abstract

A connecting assembly comprising an air distribution housing, between an air inlet passage and at least one duct connected with the housing by at least one bush mounted on an orifice of a wall of the housing. The wall of the housing and an inner wall of the bush are connected by a fillet having a radius which is maximum over an angular sector.

First claim

The invention claimed is:

1. A turbine engine for an aircraft, comprising:
a connecting assembly comprising:
a housing for distributing air between an air inlet passage of the housing and a plurality of ducts via a plurality of orifices of a first wall of the housing,
a plurality of bushes, each of said plurality of bushes connecting a respective one of the plurality of ducts to a respective one of the plurality of orifices to allow air to circulate in contact with an inner wall of the respective bush and in a first direction from the housing into the respective duct, and
a plurality of fillets each configured to connect an inner wall of a respective one of the plurality of bushes to a respective inside portion of said first wall of the housing, and having a radius which varies over at least a part of a perimeter of said inner wall to divert air from a second direction within the housing to the first direction, the first direction being different than the second direction; and

an outer casing of a turbine of the turbine engine, about a zone of which is positioned the housing for distributing air, a second wall of which extends to be adjacent to said zone of the outer casing.

2. The turbine engine of claim 1 , wherein said each of said plurality of bushes has an outer wall having a plurality of flat lugs positioned angularly, about said axis, at a distance from a zone of the perimeter where the radius of the fillet tends towards a maximum.

3. The turbine engine of claim 1 , wherein:
the air inlet passage and a respective orifice of each of the plurality of bushes have centers through which respective straight lines pass, and
the radius of each fillet is maximum over an angular sector centered on the corresponding straight line, open towards the air inlet passage which air comes from, and ranging from 90 to 135°.

4. The turbine engine of claim 1 , wherein each of the plurality of ducts has an inner diameter between 12 and 26 centimeters and the radius of the fillet varies from 0.5 to 7 centimeters.

5. The turbine engine of claim 1 , wherein the radius of each of the plurality of fillets tends to a maximum at a place of a zone of the perimeter of said respective inner wall which is oriented towards the air inlet passage.

6. The turbine engine of claim 1 , wherein each of the plurality of bushes is mounted on a respective orifice of the housing to be adjacent to said second wall of the housing, and has an outer wall provided, on a periphery, with at least one flat lug which, on at least one of the plurality of bushes, is positioned adjacent to said second wall of the housing, so as to position the plurality of orifices of the respective housing, the plurality of bushes, and the plurality of ducts as close to the outer casing of the turbine as possible.

7. The turbine engine of claim 1 , wherein each of the plurality of bushes is mounted on a respective orifice of the housing and has, on a periphery, a plurality of flat lugs positioned angularly, about said axis, at a distance from said zone of the perimeter.

8. A turbine for a turbine engine, the turbine engine comprising:
a connecting assembly comprising:
a housing for distributing air between an air inlet passage of the housing and a plurality of ducts via a plurality of orifices of a first wall of the housing;
a plurality of bushes, each of said plurality of bushes connecting a respective one of the plurality of ducts to a respective one of the plurality of orifices to allow air to circulate in a first direction from the housing into the respective duct; and
a plurality of fillets each configured to connect an inner wall of a respective one of the plurality of bushes to a respective inside portion of said first wall of the housing, each of said plurality of fillets having a radius which varies over at least a part of a perimeter of said inner wall to change the direction of air from a second direction within the housing to the first direction, the first direction being different than the second direction; and

an outer casing of the turbine, about a zone of which is positioned the housing for distributing air, a second wall of which extends to be adjacent to said zone of the outer casing.

9. The turbine of claim 8 , wherein each of said plurality of bushes has an outer wall having a plurality of flat lugs positioned angularly, about said axis, at a distance from a zone of the perimeter where the radius of the respective fillet of the plurality of fillets tends towards a maximum.

10. A turbine engine for an aircraft, comprising:
the turbine of claim 8 , wherein each of the plurality of bushes is arranged such that air changing from the second direction to the first direction circulates in contact with an inner wall of said bush.

Assignees

• Safran Aircraft Engines

Inventors

• Prestel Sébastien Jean Laurent
• Jouy Baptiste Marie Aubin Pierre

Classifications

• F01D11/24 Primary

  by selectively cooling-heating stator or rotor components · CPC title

• F02C7/18 Primary

  the medium being gaseous, e.g. air {(F02C7/125 takes precedence)} · CPC title

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title

• F02C7/20

  Mounting or supporting of plant; Accommodating heat expansion or creep · CPC title

• F05D2250/20

  Three-dimensional · CPC title