U.S. patent application 20190078516 (applicant General Electric Co., Schenectady, N.Y.):
"A gas turbine engine having a heat absorption device and an associated method are disclosed. The gas turbine engine includes a compressor, a combustor, a turbine, a bleed fluid cavity, and the heat absorption device. The combustor is coupled to the compressor. The turbine is coupled to the compressor and the combustor. The bleed fluid cavity is formed at a first predefined location in the compressor. The heat absorption device is disposed in the bleed fluid cavity and includes a casing, a flow path, and a phase change material. The casing includes an inlet and an outlet. The flow path is within the casing, extends between the inlet and the outlet, and directs an input bleed fluid separated from a fluid stream discharged from the compressor. The phase change material is filled in the casing, separated from the flow path."