Pressure regulating valve assembly

A gas turbine engine for an aircraft comprising:

• an engine core comprising a turbine, a compressor, and a core shaft connecting the turbine to the compressor,
• a nacelle having an intake lip,
• an anti-ice system that provides bleed air from the compressor to the nacelle intake lip for heating the intake lip, and
• a pressure regulating valve assembly which is configured to regulate an amount of bleed air provided to the intake lip, the pressure regulating valve assembly comprising:
• a valve having an upstream side receiving an input flow and a downstream side providing an output flow,
• an actuator configured for opening and closing the valve, including partially opening the valve,
• a regulator configured for controlling the actuator to open or close the valve or to partially open the valve,
• wherein the regulator comprises a sense pressure port, wherein a pressure present at the sense pressure port is maintained constant by the regulator,
• a chamber having a first entry orifice, a second entry orifice and an exit orifice, wherein the first entry orifice is connected to the valve upstream side, the second entry orifice is connected to the valve downstream side, and the exit orifice is connected to the sense pressure port, wherein the exit orifice is provided such that a pressure present at the exit orifice which is applied to the sense pressure port lies between a pressure at the first entry orifice and a pressure at the second entry orifice.