I'm asking this question since I can't intuitively understand how the acceleration of mass flow and therefore the increase of its momentum can actually mechanically act on the combustion chamber walls and nozzle walls to induce momentum thrust.
For example, when it comes to pressure thrust induced by pressure recovery at various diffuser sections within a propulsion system, it is easy to understand that the parallel component of the force (parallel to the axis of total thrust vector) acting on the diffuser walls of the inlet, compressor diffuser, compressor stator blades, etc will induce an asymmetric load and therefore result in forward thrust. It is also intuitively understandable how the propeller/fan/compressor of gas turbine engines will induce thrust, since it is mechanically altering the mass flow, giving it more momentum and as a result of conservation of momentum, an opposing momentum, i.e. momentum thrust will occur on the individual propeller/fan/compressor blade.
Though, how does the reaction force actually act on combustion chamber/afterburner or nozzle walls? For example, from what I understand the combustion chamber and the afterburner of the gas turbine engine is a constant pressure device so it's not an increase in pressure load acting on the engine compartment that is resulting in thrust when it comes to combustion chambers of gas turbines. The way I understand combustion is that it adds heat energy to the mass flow, and subsequently some of that energy will do work and get converted into kinetic energy resulting in increased mass flow velocity. I can understand that somehow, the expanded gas would be interacting with the chamber wall mechanically resulting in increase of momentum and reactionary force, but it's just not intuitive enough and I'd like to have some better explanation to it.
As for the nozzle, according to NASA's beginner's guide to aeronautics nozzle is not doing any thermodynamic work and there's no pressure change throughout the nozzle. Though this seems a bit counterintuitive to me since my understanding is that a nozzle decreases the pressure of mass flow and increases its velocity. For such reason it is also not understandable to me how the nozzle exit speed greatly influences total thrust when there is no thermodynamic work involved (i.e. conversion of thermal energy into kinetic work, increasing momentum); it must mean that I'm not understanding some basic fundamentals correctly.