By 1961, the pintle injector was developed into a design usable in rocket engines, and subsequently, the pintle injector design was matured and developed by a number of TRW employees, adding such features as throttling, rapid pulsing capability, and face shutoff.

Jul 7, 2022 · Pintle. The pintle injector design typically consists of just one element and works by impinging a central radial flow with an outer axial flow as shown below.

A pintle is a pin or bolt, usually inserted into a gudgeon, which is used as part of a pivot or hinge. Other applications include pintle and lunette ring for towing, and pintle pins securing casters in furniture.

Sep 12, 2019 · In this study, a design methodology is developed for a pintle injector. Following this methodology, a 750 N pintle injector is designed and then analyzed by computational fluid dynamics (CFD...

Dec 20, 2016 · To achieve proper performance under all throttling conditions, a design procedure was established for a pintle injector based on spray characteristics. The spray angle and Sauter mean diameter of the droplets were critical performance parameters.

liquid bipropellant rocket engines. The pintle injector design can deliver high combustion efficiency (typically 96–99%) and enables implementing some unique operating features, such as deep throttling and injector face shutoff. Its design simplicity makes it ideally suited for use on low cost engines. Significantly lower development and

Pintle injector design methodology for liquid oxygen/gaseous methane rocket engine is investigated with this study. Cold flow experimental work is conducted with water and air to investigate the characteristics of designed injectors by observing spray formations. 750N at maximum thrust with 3:1 throttle ability is chosen as mission requirement.

Pintle injector design for all PSAS liquid propellant engines - psas/pintle-injector

Pintle injector design for all PSAS liquid propellant engines - psas/pintle-injector

The pintle injector design is fundamentally based upon obtaining a mechanical interlock of the propellants, which forces liquid phase mixing to occur. Selection of a oxidizer-centered or fuel-centered pintle design can be established