Variable Throat Nozzle Assembly for Turbine Engine

The patent applies the dynamics principle by making the effective throat area variable rather than fixed. The nozzle geometry is dynamically adjusted during operation through the injection of cooling fluid into the boundary layer, which modifies the flow characteristics and effectively changes the throat size. This allows the engine to optimize between thrust and efficiency based on operational conditions, resolving the contradiction between maximizing thrust and maintaining efficiency.

The patent changes the parameter of effective throat area by introducing a controllable variable. By injecting fluid into the boundary layer at the nozzle inlet, the flow characteristics change, effectively altering the throat area. This parameter change enables the system to transition between high-thrust and high-efficiency operating modes, directly addressing the contradiction between thrust generation and engine efficiency.

The patent segments the cooling function from the thrust generation function. Instead of relying on a single large cooling passage that would reduce thrust, the cooling fluid is introduced through multiple small exhaust holes distributed across the airfoil surface. This segmentation allows adequate cooling coverage while minimizing the impact on the effective throat area and thrust generation.

The patent applies local quality by providing cooling fluid at specific locations (through exhaust holes in the airfoil) rather than uniform cooling throughout. The cooling is concentrated where needed in the boundary layer to prevent separation and maintain flow attachment, while the majority of the throat area remains free for thrust-generating flow.

The patent applies self-service by using the engine's own cooling fluid system to achieve variable throat functionality. The existing cooling fluid supplied to the turbine is redirected through the airfoil interior passage and exhausted through holes in the airfoil surface. This self-service approach utilizes available resources within the engine system to achieve performance optimization without adding external complex mechanisms.

The airfoil structure serves multiple functions: it guides the main flow for thrust generation, provides structural support for the turbine stage, and acts as a cooling duct by incorporating interior passages and exhaust holes. This multi-functionality reduces the need for separate variable throat mechanisms, thereby limiting the increase in device complexity while achieving adaptability.