Nose-Cowl Generator Integration in Gas Turbines for Compact Maintenance
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Solution Overview
Problem
Existing gas turbines face challenges in optimizing space utilization, accessibility, and thermal conditions for electrical generators within the turbine assembly, particularly in aircraft engines, which affects their compactness, maintenance, and operational efficiency.
Innovation Solution
Integrating an electrical generator within the nose cone of the gas turbine assembly, utilizing previously unused space and improving thermal conditions, while coupling the generator rotor to the compressor shaft for power generation, and using a housing stator for structural support.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Volume of moving object
If the electrical generator is placed inside the gas turbine assembly, then space utilization is improved and compactness is achieved, but accessibility for maintenance and thermal conditions deteriorate
Solution Approach 1:
The nose cone is designed as a separable component that can be removed independently from the gas turbine assembly. This segmentation allows the generator to be accessed, removed, or maintained by simply detaching the nose cone, thereby improving ease of repair while maintaining compact integration during operation.
Solution Approach 2:
The nose cone serves as an intermediary structure that provides a removable access point to the generator. It acts as a mediator between the external environment and the internally mounted generator, allowing maintenance personnel to reach the generator without disassembling the entire turbine assembly.
2Volume of moving object
If the electrical generator is placed inside the gas turbine assembly, then compactness is improved, but thermal conditions for the generator deteriorate
Solution Approach 1:
The nose cone region is designed with specific thermal characteristics that are more favorable for generator placement compared to other parts of the turbine assembly. This local quality improvement provides a relatively cooler and more stable thermal environment for the generator while maintaining overall compactness.
3Ease of repair
If the nose cone is made separable for maintenance access, then ease of repair is improved, but structural complexity increases
Solution Approach 1:
The nose cone is divided into separable parts that can be easily detached and reattached. This segmentation simplifies the maintenance process by allowing quick access to the generator without requiring complex disassembly procedures, thereby improving ease of repair with minimal increase in structural complexity.
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
Enhances space utilization, improves maintenance accessibility, and optimizes thermal conditions, resulting in a more compact, efficient, and robust gas turbine design.
Implementation Method 1
a generator rotor ("generator rotor") is coupled to the compressor shaft, preferably non-rotatably and/or at least temporarily and/or directly or indirectly, or integrally formed. This allows rotation of the compressor shaft about its axis of rotation relative to the housing stator to rotate the generator rotor relative to the generator stator, so that the generator supplies electrical current, at least temporarily.
Data Source
Figure 1
AI summary
The present invention relates to a gas turbine assembly, in particular a gas turbine and/or for an aircraft engine, wherein the gas turbine assembly comprises a casing stator (1), a compressor shaft (2) with an axis of rotation (R), and an electric generator, wherein a generator stator (31) of the generator is connected to or integrally formed with the casing stator, a generator rotor (32) of the generator is coupled to or integrally formed with the compressor shaft, and the generator is at least partially enclosed in a nose cowl (11) arranged on the casing stator. The invention further relates to an aircraft engine and a method for manufacturing, maintaining, and/or operating the gas turbine assembly.