US 12,435,683 B2
Rocket injector subscale stability assessment with telescoping throat or moveable injector plate
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. 18/510,359.
Claims priority of provisional application 63/477,633, filed on Dec. 29, 2022.
Prior Publication US 2024/0218846 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)] 20 Claims
OG exemplary drawing
 
1. A system for subscale testing of rocket injector stability, the system comprising:
a chamber having a sidewall extending axially;
a throat at a downstream end of the chamber; and
an injector plate spanning across a cross-section of the chamber to provide a barrier at an upstream end of the chamber, the injector plate removably positioned at an upstream end of the chamber, the injector plate comprising 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, wherein the injector plate is continuously moveable through the chamber between the sidewall in an axial direction to continuously vary a combustion volume of the chamber located between the injector plate and the throat, and wherein the chamber is configured to have a single injector plate attached to the chamber during testing.