Rotary Valve Combustion Module for Turbine Sealing
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Existing combustion chambers for aircraft turbomachines operating on constant-volume cycles face issues with robustness, tightness, and complexity, particularly in the design of rotary and spherical valves, leading to friction, manufacturing difficulties, and inefficient sealing, which affect the longevity and efficiency of the turbomachine.
Innovation Solution
A combustion module with a radiating structure featuring a common rotary inlet and exhaust valve system, where each combustion chamber is coaxially arranged around an internal tubular crankcase and an outer tubular casing, allowing synchronized operation and phase shifting to optimize gas flow and reduce pulsation, thereby simplifying the architecture and enhancing sealing.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If spherical valves with spherical rotors are used to improve sealing, then sealing performance is improved, but friction increases significantly
Solution Approach 1:
The patent uses spherical rotors and spherical casings to create a curved surface contact that improves sealing performance. The spherical geometry allows for better conformal contact between mating surfaces, reducing gas leakage while maintaining manageable friction through proper lubrication and surface treatment.
2Reliability
If spherical valves with spherical rotors are used to improve sealing, then sealing performance is improved, but manufacturing difficulty increases
Solution Approach 1:
The spherical geometry of rotors and casings, while challenging to manufacture, can be produced using modern techniques such as investment casting, precision forging, or additive manufacturing. The spherical shape simplifies assembly and reduces the number of mating surfaces, offsetting some manufacturing complexity.
3Adaptability or versatility
If independent synchronized valves are used for each chamber, then individual chamber control is improved, but device complexity increases
Solution Approach 1:
The patent combines multiple valve functions into a single integrated spherical rotor assembly where multiple intake and exhaust valves are formed by radial slots in the rotor. This single rotating component simultaneously controls all chambers, eliminating the need for separate synchronized valve mechanisms for each chamber while maintaining individual chamber control through the rotor's rotational position.
4Ease of operation
If rotary valves with ovoid cross-section elements are used, then valve operation is simplified, but sealing performance deteriorates
Solution Approach 1:
The patent transitions from ovoid cross-section elements to spherical rotors with radial slots. The spherical geometry provides better sealing contact through conformal surfaces, while the radial slots maintain simple rotational operation. The spherical rotor rotates within a spherical casing, creating reliable sealing at the contact surfaces while preserving ease of operation through single-degree-of-freedom rotation.
Data Source
Figure 1~5
Figure 6~7
Figure 8~14
AI summary
The invention relates to a turbine engine combustion module (10), in particular for an aircraft turbine engine, designed to carry out constant-volume combustion, comprising: a plurality of combustion chambers (12) distributed angularly in a regular manner about an axis (A), each chamber (12) comprising a compressed gas intake port (16) and a burnt gas exhaust port (18), each intake (16)/exhaust (18) port being designed to be opened or closed by a corresponding common intake (28)/exhaust (30) rotary valve coaxial with the axis (A). The invention also relates to a turbine engine comprising a combustion module (10) of the type described.