US 12,392,303 B2
Degassing tube and ejection cone for a turbine engine, as well as tool for assembly thereof
Samuel Louis-Marie Bernard, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR)
Filed on Mar. 2, 2022, as Appl. No. 17/653,245.
Application 17/653,245 is a division of application No. 15/769,060, granted, now 11,306,679, previously published as PCT/FR2016/052765, filed on Oct. 25, 2016.
Claims priority of application No. 1560563 (FR), filed on Nov. 4, 2015.
Prior Publication US 2022/0186681 A1, Jun. 16, 2022
Int. Cl. F02K 1/04 (2006.01); F01D 25/28 (2006.01); F02C 7/06 (2006.01)
CPC F02K 1/04 (2013.01) [F01D 25/285 (2013.01); F02C 7/06 (2013.01); F05D 2220/323 (2013.01); F05D 2230/64 (2013.01); F05D 2230/644 (2013.01); F05D 2250/131 (2013.01); F05D 2250/132 (2013.01); F05D 2260/30 (2013.01); F05D 2260/605 (2013.01); F05D 2260/608 (2013.01); F05D 2260/609 (2013.01)] 11 Claims
OG exemplary drawing
 
1. Locating and adjusting tool for the assembly of a unit of a turbine engine of an aircraft, the unit comprising a degassing tube and an ejection cone,
the degassing tube having an extended form and comprising first fixing means configured to fix to a first element of the turbine engine at a first longitudinal end, the degassing tube also comprising first centering means which are located at an external periphery of the degassing tube and at a distance from said first longitudinal end, said first centering means being configured to co-operate with second centering means of the ejection cone which is designed to be traversed by said degassing tube, said first centering means having a polygonal cross-sectional profile and being formed by external flat surfaces of the degassing tube that extend annularly around an outside of the degassing tube,
the ejection cone having an extended form and comprising second fixing means configured to fix to a second element of the turbine engine at a second longitudinal end, the ejection cone also comprising the second centering means which are located at an inner periphery of the ejection cone and at a distance from said second longitudinal end, said second centering means being configured to co-operate with said first centering means of the degassing tube which is designed to traverse said ejection cone, the ejection cone comprising at least one annular stiffener at the inner periphery, said second centering means being fixed in a detachable manner to said at least one annular stiffener, said second centering means comprising an annular row of tabs configured to be supported radially on said first centering means,
wherein the locating and adjusting tool comprises:
a first ring configured to be applied and fixed to said second element of the turbine engine and to also be, in a sequence manner, applied and fixed to the second longitudinal end of larger diameter of said ejection cone, said first ring being configured to be traversed by said degassing tube,
a second ring configured to be traversed by said degassing tube and to be accommodated in said ejection cone,
ring connecting struts, which extend between the first and second rings and are fixed to the first and second rings, these ring connecting struts being configured to be accommodated in said ejection cone, and
a third ring configured to be traversed by said degassing tube and to carry, in a detachable and sequenced manner, a tubular finger of the locating and adjusting tool, said tubular finger comprising third centering means substantially identical to said first centering means of said degassing tube, said third centering means having a polygonal cross-sectional profile and being formed by external flat surfaces of the tubular finger that extend annularly around an outside of the tubular finger, said third ring being directly fixed on said second ring by fourth means allowing an adjustment of a radial misalignment of axes of said second and third rings, said fourth means comprising an annular row of first screws, the first screws being carried by the third ring.