Patent ID: 9657844
Date: 2017-05-23
CPC Classifications: F01D,F02C,F04D,F05D,F16K,Y02T,Y10T

Claim:
1. A valve unit for an aircraft, comprising: a valve assembly; a servo controller coupled to the valve assembly and configured to control operation of the valve assembly, wherein at least a portion of at least one of the valve assembly and servo controller is formed by a high temperature aluminum alloy, wherein the valve assembly is configured to modulate a flow of air, the servo controller being configured to at least partially pneumatically control the valve assembly with a portion of the air; a heat exchanger coupled to the servo controller and the valve assembly, the heat exchanger configured to receive the portion of the air from the valve assembly and to provide the portion of the air to the servo controller, the heat exchanger configured to remove heat from the portion of the air after receiving the portion of the air from the valve assembly and prior to providing the portion of the air to the servo controller, wherein the heat exchanger defines a plurality of passages with a serpentine pattern for removing the heat from the portion of the air, wherein the servo controller has a first side and a second side, opposite to the first side; at least one first bracket mounting the first side of the servo controller to the valve assembly; and at least one second bracket mounting the second side of the servo controller to the heat exchanger.