Cross-Diffuser Bleed Routing in Radial Diffusers
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Solution Overview
Problem
Existing bleed air systems in gas turbine engines require external routing of compressed air, which adds weight, maintenance complexity, and reduces engine performance due to external components, limiting range and increasing fuel consumption.
Innovation Solution
The implementation of an internal bleed air system within the gas turbine engine using a radial diffuser with integrated bleed conduits and passages to route bleed air from the forward to the aft side, eliminating external components and reducing weight and maintenance needs.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Quantity of substance
If external routing of compressed air is used, then bleed air can be provided to aircraft systems, but weight increases and maintenance complexity increases
Solution Approach 1:
The patent combines the bleed air routing function with the diffuser structure by integrating bleed conduits directly into the diffuser vanes. This merging eliminates separate external routing components and reduces overall system weight while maintaining the ability to supply bleed air to aircraft systems.
Solution Approach 2:
The bleed conduits are nested within the diffuser vane structure, with conduits positioned between adjacent diffuser vanes. This nesting approach allows the bleed air system to be contained within the existing diffuser assembly, reducing external components and weight.
2Quantity of substance
If external routing components are used, then bleed air distribution is achieved, but maintenance complexity increases
Solution Approach 1:
By merging the bleed air routing function into the diffuser structure itself, the patent reduces the number of separate components that require maintenance. The integrated design eliminates external routing components, simplifying the overall system and reducing maintenance complexity.
Solution Approach 2:
The diffuser structure serves dual functions: both airflow diffusion for combustion and bleed air routing. This self-service approach where one component performs multiple functions reduces system complexity and maintenance requirements compared to separate dedicated routing components.
3Quantity of substance
If external components are used for bleed air routing, then air can be routed from compressor to aircraft systems, but reliability decreases due to damage risks
Solution Approach 1:
The patent merges the bleed air routing function into the protected internal environment of the diffuser assembly, eliminating exposure of routing components to external damage risks during installation and operation. The integrated conduits are shielded within the engine structure.
Solution Approach 2:
The patent extracts the vulnerable external routing components and replaces them with internally integrated conduits. By taking out the external routing function and incorporating it directly into the diffuser structure, the system eliminates components susceptible to external damage.
4Weight of moving object
If internal bleed air system is used, then weight is reduced and maintenance is minimized, but device complexity must be managed
Solution Approach 1:
The diffuser structure is designed to serve multiple functions: primary airflow diffusion for combustion and integrated bleed air routing. This multi-functionality reduces the need for separate components, lowering weight while managing complexity through functional integration.
Solution Approach 2:
By combining multiple functions (diffusion and bleed routing) into a single integrated structure, the patent reduces overall system weight and component count. The merging of functions eliminates the need for separate external routing components.
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
This approach reduces the weight and part count of the bleed air system, improves durability, and enhances maintainability by integrating the system entirely within the engine, thereby improving engine performance and reducing nacelle drag.
Implementation Method 1
Diffusers include a plurality of diffuser vanes to aid in reducing the velocity of the compressed airflow
Implementation Method 2
The bleed air system is integrated internally within the gas turbine engine, utilizing a radial diffuser with bleed conduits to route compressed air from the forward to the aft side
Data Source
AI summary
Systems, apparatus, articles of manufacture, and methods to provide for cross-diffuser bleed are provided herein. An example gas turbine engine includes a frame defining a cavity in a forward side of a diffuser of the gas turbine engine; a compressor including the diffuser, the diffuser defining a primary flow path to provide air flow to a combustor and including at least one conduit, the at least one conduit fluidly coupled to the cavity; and a downstream sink fluidly coupled to the cavity via the at least one conduit defining at least a portion of a bleed air path.