The invention relates to a gas turbine (13) comprising an intake tract (14) and a compressor (1) having a compressor flow channel (4). The compressor (1) further comprises an inlet guide vane row (3) positioned in the compressor flow channel (4) having inlet guide vanes that can be adjusted. According to the invention, the gas turbine (13) has an icing sensor unit (17) having at least one sensor arranged between a first compressor blade row (5) and a first compressor guide vane row (6). The first compressor blade row (5) is thereby arranged in the compressor flow channel (4) directly downstream of the inlet guide vane row (3), and the first compressor guide vane row (6) is arranged directly downstream of the first compressor blade row (5). The invention further relates to a method (18), wherein an imminent icing of the compressor (1) is detected, and the compressor (1) is safeguarded therefrom such that at least inlet guide vanes of the inlet guide vane row (3) are adjusted such that the acceleration of an intake air mass flow (12) is reduced.