Invention Grant
US08162591B2 Multistage compressor for a gas turbine, comprising discharge ports and injection ports to stabilize the compressor flow
有权
用于燃气轮机的多级压缩机，包括排出口和喷射口以稳定压缩机流量
- Patent Title: Multistage compressor for a gas turbine, comprising discharge ports and injection ports to stabilize the compressor flow
- Patent Title (中): 用于燃气轮机的多级压缩机，包括排出口和喷射口以稳定压缩机流量
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Application No.: US12092221Application Date: 2006-10-26
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Publication No.: US08162591B2Publication Date: 2012-04-24
- Inventor: Frank Grauer
- Applicant: Frank Grauer
- Applicant Address: DE Munich
- Assignee: MTU Aero Engines GmbH
- Current Assignee: MTU Aero Engines GmbH
- Current Assignee Address: DE Munich
- Agency: Greer, Burns & Crain, Ltd.
- Priority: DE102005052466 20051103
- International Application: PCT/DE2006/001889 WO 20061026
- International Announcement: WO2007/051444 WO 20070510
- Main IPC: F01D25/24
- IPC: F01D25/24
Abstract:
A multistage compressor for a gas turbine, having a compressor housing, guide vanes, impeller vanes, a hub area, discharge ports, and injection ports for stabilizing the compressor flow, wherein the discharge ports are situated at least one stage downstream from the injection ports, the injection ports being fashioned as nozzles, and the geometry of these nozzles is designed such that the flow speed of the injected air stream is significantly greater than the speed of the flow in a critical cross-section.
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