CPC B64D 37/30 (2013.01) [B64D 27/12 (2013.01); B64D 37/04 (2013.01); B64D 37/32 (2013.01); F02C 3/22 (2013.01); F02C 7/20 (2013.01); F02C 7/222 (2013.01)] | 9 Claims |
1. A powerplant for an aircraft comprising:
a frame,
a propulsion system fastened to the frame and comprising a core enclosed in a casing and comprising a combustion chamber and a turbine provided with blades rotating about a longitudinal axis,
a supply pipe for conveying dihydrogen to the combustion chamber, in which the supply pipe snakes outside the casing running along the turbine before dropping down into the combustion chamber through the casing, and
a protective plate fastened to the frame by fastening means and positioned between the casing and the supply pipe and between the supply pipe and the turbine, the powerplant,
wherein the fastening means comprise a front fastening system arranged at a front part of the protective plate and two lateral fastening systems positioned on either side of a vertical mid-plane of the protective plate behind the front part, where the front fastening system comprises a front rod hingedly fastened by a first connection point to the frame at the mid-plane of the protective plate and by two second connection points to the protective plate, in which the second connection points are positioned on either side of the mid-plane of the protective plate, and
wherein each lateral fastening system comprises a lateral rod hingedly fastened by a first connection point to the frame and by two second connection points to the protective plate.
|