US 12,123,313 B2
In-flight measured propulsion mass flow and thrust on aircraft
Kevin Todd Lowe, Blacksburg, VA (US); Gwibo Byun, Blacksburg, VA (US); and Albert P. Krejmas, Wethersfield, CT (US)
Assigned to RTX CORPORATION, Farmington, CT (US)
Filed by RTX Corporation, Farmington, CT (US)
Filed on Jul. 2, 2021, as Appl. No. 17/366,654.
Prior Publication US 2023/0013891 A1, Jan. 19, 2023
Int. Cl. F01D 21/00 (2006.01); B64D 27/18 (2006.01); B64D 43/00 (2006.01); F02C 9/00 (2006.01); G01F 1/661 (2022.01)
CPC F01D 21/003 (2013.01) [B64D 27/18 (2013.01); B64D 43/00 (2013.01); F02C 9/00 (2013.01); G01F 1/661 (2013.01); F05D 2220/323 (2013.01); F05D 2260/80 (2013.01); F05D 2270/3061 (2013.01); F05D 2270/804 (2013.01)] 6 Claims
OG exemplary drawing
 
1. An optically-based measurement system comprising:
a first imaging system disposed adjacent an inlet of a gas turbine engine of an aircraft, the first imaging system configured to perform a first imaging of a first target area of the inlet of the gas turbine engine of the aircraft to generate a targeted inflow spectrum, the first imaging performed while the gas turbine engine operates while the aircraft is in flight;
a second imaging system disposed adjacent an outlet of the engine, the second imaging system configured to perform a second imaging of a second target area of the outlet of the gas turbine engine of an aircraft to generate a targeted outflow spectrum, the second imaging performed while the gas turbine engine operates while the aircraft is in flight; and
a measurement controller configured to calculate a first mass flow and a second mass flow of the gas turbine engine based at least in part on the first imaging of the inlet and the second imaging of the outlet, respectively,
wherein based on the first mass flow the measurement controller determines an inflow temperature (T1), an inflow density (ρ1), and an inflow velocity magnitude (U1), and determines an inlet momentum flux based on the inflow temperature (T1), the inflow density (ρ1), and the inflow velocity magnitude (U1),
wherein based on the second mass flow the measurement controller determines an outflow temperature (T2), an outflow density (ρ2) and an outflow velocity magnitude values (U2), and determines an outlet momentum flux based on the outflow temperature (T2), the outflow density (ρ2) and the outflow velocity magnitude values (U2),
wherein the inflow temperature (T1), the inflow density (ρ1), and the inflow velocity magnitude (U1) are determined by comparing the targeted inflow spectrum to one or more first stored inflow spectrum models, and then extracting the inflow temperature value (T1), the inflow density value (ρ1), and the inflow velocity magnitude value (U1) that defines a matching inflow spectrum model,
wherein the outflow temperature (T2), the outflow density (ρ2), and the outflow velocity magnitude (U2) are determined by comparing the targeted outflow spectrum to one or more stored outflow spectrum models, and then extracting the outflow temperature value (T2), the outflow density value (ρ2), and the outflow velocity magnitude value (U2) that defines a matching outflow spectrum model, and
wherein the measurement controller is configured to calculate a thrust force of the gas turbine engine while the aircraft is in flight based on a difference between the inlet momentum flux and the outlet momentum flux.