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Patent Agency Ranking
公开(公告)号：US20170074271A1
公开(公告)日：2017-03-16
申请号：US15245388
申请日：2016-08-24
Applicant: MTU Aero Engines AG
Inventor： Werner Humhauser , Roland Matzgeller
CPC classification number: F04D29/324 , F04D19/028 , F04D29/544 , F05B2220/303 , F05D2220/323 , F05D2250/70
Abstract: The present invention relates to a compressor stage for a gas turbine, in particular, an aircraft engine, having a row of rotating blades (3) and a row of guide vanes (4), which is adjacent downstream, wherein the choke point σ and the aspect ratio ARax, which is defined by the quotient between average channel height (h) and average chord length (lax), satisfy the condition σ>−1.33×ARax+5.16.
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公开(公告)号：US12123419B2
公开(公告)日：2024-10-22
申请号：US18345319
申请日：2023-06-30
Applicant: MTU Aero Engines AG
Inventor： Sergio Elorza Gomez , Werner Humhauser , Roland Matzgeller
Abstract: The invention relates to a compressor for an engine, wherein the compressor has compressor stages arranged in succession in a flow direction of the compressor and each compressor stage has a rotating blade cascade and a guide vane cascade arranged downstream of the rotating blade cascade and the rotating blade cascade and the guide vane cascade each have an aspect ratio.
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公开(公告)号：US10280934B2
公开(公告)日：2019-05-07
申请号：US15245388
申请日：2016-08-24
Applicant: MTU Aero Engines AG
Inventor： Werner Humhauser , Roland Matzgeller
Abstract: The present invention relates to a compressor stage for a gas turbine, in particular, an aircraft engine, having a row of rotating blades (3) and a row of guide vanes (4), which is adjacent downstream, wherein the choke point σ and the aspect ratio ARax, which is defined by the quotient between average channel height (h) and average chord length (lax), satisfy the condition σ>−1.33·ARax+5.16.
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公开(公告)号：US20240011434A1
公开(公告)日：2024-01-11
申请号：US18345836
申请日：2023-06-30
Applicant: MTU Aero Engines AG
Inventor： Sergio Elorza Gomez , Werner Humhauser , Roland Matzgeller
IPC: F02C3/06
CPC classification number: F02C3/06
Abstract: The invention is directed to an engine that has a fan, a compressor with a high-pressure compressor, and a combustion chamber. The high-pressure compressor of the engine has a mean stage pressure ratio and an overall pressure ratio formed between the fan and the combustion chamber.
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公开(公告)号：US20240003353A1
公开(公告)日：2024-01-04
申请号：US18345319
申请日：2023-06-30
Applicant: MTU Aero Engines AG
Inventor： Sergio Elorza Gomez , Werner Humhauser , Roland Matzgeller
Abstract: The invention relates to a compressor for an engine, wherein the compressor has compressor stages arranged in succession in a flow direction of the compressor and each compressor stage has a rotating blade cascade and a guide vane cascade arranged downstream of the rotating blade cascade and the rotating blade cascade and the guide vane cascade each have an aspect ratio.
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