US 12,404,823 B2
Rocket injector subscale stability assessment with telescoping piston
Owen Graham, Issaquah, WA (US); Warren Lamont, Seattle, WA (US); and James Sisco, Goffstown, NH (US)
Assigned to Blue Origin Manufacturing, LLC, Huntsville, AL (US)
Filed by Blue Origin Manufacturing, LLC, Huntsville, AL (US)
Filed on Nov. 15, 2023, as Appl. No. 18/510,495.
Claims priority of provisional application 63/477,633, filed on Dec. 29, 2022.
Prior Publication US 2024/0218845 A1, Jul. 4, 2024
Int. Cl. F02K 9/52 (2006.01); F02K 9/42 (2006.01); F02K 9/64 (2006.01); F02K 9/86 (2006.01); F02K 9/96 (2006.01); F02K 9/97 (2006.01); G01M 15/14 (2006.01)
CPC F02K 9/52 (2013.01) [F02K 9/42 (2013.01); F02K 9/64 (2013.01); F02K 9/86 (2013.01); F02K 9/96 (2013.01); F02K 9/97 (2013.01); F02K 9/978 (2013.01); G01M 15/14 (2013.01)] 22 Claims
OG exemplary drawing
 
1. A system for subscale testing of rocket injector stability, the system comprising:
a chamber having a sidewall extending axially;
an injector plate removably attached to an upstream end of the chamber, the injector plate structurally holding one or more injectors configured to inject one or more propellants into the chamber, the injector plate being one of a plurality of different injector plates configured to be removably attached to the chamber for interchanging the injector plate with a different injector plate of the plurality of different injector plates, the different injector plate structurally holding one or more different injectors; and
a piston positioned at least partially within the chamber, the piston comprising a head on an upstream end thereof and an extension rod extending downstream from the head through a downstream exit of the chamber, wherein the piston is continuously moveable in an axial direction to continuously vary a combustion volume of the chamber located between the injector plate and the upstream end of the piston.