US 12,203,416 B2
Transducer assemblies that selectively measure a fuel pressure within a fuel supply system of an aircraft, aircraft that include the transducer assemblies, and methods of utilizing a transducer assembly to test performance of a fuel boost pump assembly of an aircraft
Matthew A. Couture, Krum, TX (US)
Assigned to The Boeing Company, Arlington, VA (US)
Filed by The Boeing Company, Chicago, IL (US)
Filed on Oct. 13, 2022, as Appl. No. 17/965,627.
Prior Publication US 2024/0125273 A1, Apr. 18, 2024
Int. Cl. F02C 7/22 (2006.01); G01L 19/00 (2006.01); G01L 19/08 (2006.01)
CPC F02C 7/22 (2013.01) [G01L 19/0007 (2013.01); G01L 19/083 (2013.01)] 17 Claims
OG exemplary drawing
 
1. A transducer assembly configured to selectively measure a fuel pressure within a fuel supply system of an aircraft, wherein the fuel pressure is generated by a fuel boost pump assembly of the aircraft, and further wherein the fuel boost pump assembly includes a pressure switch receptacle, which includes a receptacle valve that defines a nominally closed configuration and is configured to receive a pressure switch, the transducer assembly comprising:
an electronic pressure transducer configured to measure the fuel pressure and to generate a fuel pressure signal indicative of the fuel pressure;
an electronic pressure display configured to receive the fuel pressure signal and to display the fuel pressure responsive to receipt of the fuel pressure signal;
a power supply structure configured to electrically power the electronic pressure transducer and the electronic pressure display; and
an attachment structure configured to operatively interconnect the electronic pressure transducer to the aircraft, wherein the attachment structure includes:
(i) a fitting configured to interface with the pressure switch receptacle, wherein the fitting includes a fitting fastening structure configured to operatively interlock with a corresponding receptacle fastening structure of the pressure switch receptacle; and
(ii) a valve actuation structure at least partially defined by the fitting and configured to selectively actuate the receptacle valve to selectively permit fluid communication between the electronic pressure transducer and the fuel supply system via the fitting, wherein the valve actuation structure is configured to actuate the receptacle valve to permit the fluid communication responsive to the fitting fastening structure being operatively interlocked with the corresponding receptacle fastening structure of the pressure switch receptacle.