18158618. GAS TURBINE ENGINE BLEED AIR FLOW CONTROL simplified abstract (General Electric Company)
Contents
- 1 GAS TURBINE ENGINE BLEED AIR FLOW CONTROL
- 1.1 Organization Name
- 1.2 Inventor(s)
- 1.3 GAS TURBINE ENGINE BLEED AIR FLOW CONTROL - A simplified explanation of the abstract
- 1.4 Simplified Explanation
- 1.5 Potential Applications
- 1.6 Problems Solved
- 1.7 Benefits
- 1.8 Potential Commercial Applications
- 1.9 Possible Prior Art
- 1.10 Unanswered Questions
- 1.11 Original Abstract Submitted
GAS TURBINE ENGINE BLEED AIR FLOW CONTROL
Organization Name
Inventor(s)
Kudum Shinde of Boxford MA (US)
Sesha Subramanian of Liberty Township OH (US)
Yashpal Patel of Milford OH (US)
GAS TURBINE ENGINE BLEED AIR FLOW CONTROL - A simplified explanation of the abstract
This abstract first appeared for US patent application 18158618 titled 'GAS TURBINE ENGINE BLEED AIR FLOW CONTROL
Simplified Explanation
The gas turbine engine described in the patent application includes a compressor with an inner casing and an outer casing, defining a bleed air cavity between them. The inner casing also defines a first bleed air channel to energize a fluid boundary layer along the first wall.
- The compressor of the gas turbine engine has an inner casing and an outer casing.
- The inner casing creates a primary flow path for airflow through the compressor.
- A bleed air cavity is formed between the inner casing and the outer casing.
- The inner casing partially defines a first bleed air channel that connects the primary flow path to the bleed air cavity.
- The first bleed air channel is located between a first wall and a second wall, with the first wall upstream from the second wall.
- The first wall has a series of holes that allow airflow from the primary flow path to enter the first bleed air channel.
- The holes in the first wall are connected to a suction manifold to energize a fluid boundary layer along the first wall.
Potential Applications
The technology described in this patent application could be applied in aircraft engines, power generation systems, and other gas turbine applications where efficient airflow management is crucial.
Problems Solved
This innovation helps improve the efficiency and performance of gas turbine engines by optimizing airflow within the compressor and bleed air cavity.
Benefits
- Enhanced airflow management - Improved engine efficiency - Increased performance and reliability
Potential Commercial Applications
"Optimized Airflow Management in Gas Turbine Engines: Potential Commercial Applications"
Possible Prior Art
There may be prior art related to airflow management in gas turbine engines, but specific examples are not provided in the patent application.
Unanswered Questions
How does this technology impact fuel efficiency in gas turbine engines?
The patent application mentions improved efficiency and performance, but it does not delve into the specific impact on fuel consumption.
Are there any limitations to the implementation of this technology in existing gas turbine engines?
While the benefits of the innovation are highlighted, potential challenges or constraints in retrofitting this technology to current engine designs are not addressed.
Original Abstract Submitted
A gas turbine engine includes a compressor with an inner casing and an outer casing. The inner casing defines a primary flow path for airflow through the compressor, the inner casing and the outer casing define a bleed air cavity therebetween. The inner casing at least partially defines a first bleed air channel between the primary flow path and the first bleed air cavity. The first bleed air channel is defined between a first wall and a second wall, wherein the first wall is upstream from the second wall. The first wall includes a plurality of holes in fluid communication with the primary flow path and fluidly coupled to a suction manifold. The plurality of holes is configured to energize a fluid boundary layer along the first wall.
