US 12,258,874 B2
Anti-ice system for gas turbine engine and inlet guide vane
Eric Engebretsen, Indianapolis, IN (US); Aaron Weishaar, Indianapolis, IN (US); Jonathan Acker, Indianapolis, IN (US); and Brett Hartnagel, Indianapolis, IN (US)
Assigned to Rolls-Royce North American Technologies Inc., Indianapolis, IN (US)
Filed by Rolls-Royce North American Technologies Inc., Indianapolis, IN (US)
Filed on Jul. 6, 2023, as Appl. No. 18/347,722.
Prior Publication US 2025/0012202 A1, Jan. 9, 2025
Int. Cl. F01D 25/02 (2006.01); F01D 5/18 (2006.01); F02C 7/047 (2006.01)
CPC F01D 25/02 (2013.01) [F01D 5/18 (2013.01); F02C 7/047 (2013.01); F05D 2220/323 (2013.01); F05D 2240/12 (2013.01); F05D 2260/2214 (2013.01); F05D 2260/605 (2013.01)] 19 Claims
OG exemplary drawing
 
1. A gas turbine engine, comprising:
an inlet guide vane including a main body and a stem extending radially outward from the main body, the stem having an inlet for receiving anti-air ice and an outlet for discharging the anti-ice air, the stem being arranged in a stem manifold;
an inlet channel extending from a location downstream of the inlet guide vane to the stem manifold, the inlet channel configured to direct the anti-ice air to the inlet of the stem; and
an outlet channel extending to an outlet port and configured to receive the anti-ice air from the outlet of the stem, the outlet port configured to dump anti-ice air overboard,
wherein the inlet guide vane includes an anti-ice cavity in fluid communication with the inlet channel and the outlet channel such that the anti-ice air, flowing from the location downstream within a core flow of the gas turbine engine, flows from the inlet channel, into the inlet of the stem, through the anti-ice cavity of the inlet guide vane, through the outlet of the stem, and to the outlet channel,
wherein the stem is configured to rotate within the stem manifold while maintaining fluid communication with the inlet channel and the outlet channel.