Abstract: A system in one embodiment includes a heat exchanger, a detection unit, and a controller. The heat exchanger includes a first passage and a second passage configured for exchange of heat therebetween. The first passage is configured to receive a boil-off gas stream of a first cryogenic fluid. The second passage is configured to receive a liquid stream of a second cryogenic fluid. The detection unit is configured to detect a characteristic of the boil-off gas stream. The controller is configured to, responsive to information acquired from the detection unit corresponding to the characteristic, control the flow of the second cryogenic fluid to provide sufficient exchange of heat from the boil-off gas stream via the heat exchanger to condense at least a portion of the boil-off gas stream. A liquid stream of the first cryogenic fluid is output from the first passage and returned to a first tank.

Abstract: A gas turbine engine blade is laser shock peened by laser shock peening a thin airfoil of the blade, forming a laser shock induced twist in the airfoil, and shot peening a portion of the airfoil to counter the laser shock induced twist in the airfoil. The shot peening may be performed before or after the laser shock peening. The shot peening may be applied over a laser shock peened surface formed by the laser shock peening. The shot peening may be performed asymmetrically on asymmetrically shot peened pressure and suction side areas of pressure and suction sides, respectively, of the airfoil. A shot peened patch near a blade tip may be formed on one of pressure and suction sides of the airfoil wherein the airfoil extends radially outwardly from a blade platform to the blade tip of the blade.