公开(公告)号：US20180066671A1

公开(公告)日：2018-03-08

申请号：US15691858

申请日：2017-08-31

申请人： U.S. Army Research Laboratory ATTN: RDRL-LOC-I

发明人： Muthuvel Murugan ,  Anindya Ghoshal ,  Luis Bravo

IPC分类号： F04D29/32

CPC分类号： F04D29/323 ,  F01D7/00 ,  F04D27/0246 ,  F04D29/362 ,  F04D29/563 ,  F05D2260/74 ,  F05D2260/76 ,  G06F17/12 ,  G06F17/13 ,  G06F17/5018 ,  Y02T50/671 ,  Y02T50/673

摘要： Conventional gas turbine engines are generally optimized to operate at nearly a fixed speed with fixed blade geometries for the design operating condition. When the operating condition of the engine changes, the flow incidence angles may not be optimum with the blade geometries resulting in reduced off-design performance. By contrast, according to embodiments of the present invention, articulating the pitch angle of turbine blades in coordination with adjustable nozzle vanes improves performance by maintaining flow incidence angles within the optimum range at all operating conditions of a gas turbine engine. Maintaining flow incidence angles within the optimum range can prevent the likelihood of flow separation in the blade passage and also reduce the thermal stresses developed due to aerothermal loads for variable speed gas turbine applications.

公开(公告)号：US11073160B2

公开(公告)日：2021-07-27

申请号：US15691858

申请日：2017-08-31

申请人： U.S. Army Research Laboratory ATTN: RDRL-LOC-I

发明人： Muthuvel Murugan ,  Anindya Ghoshal ,  Luis Bravo

IPC分类号： F04D29/32 ,  F04D27/02 ,  F01D7/00 ,  F04D29/56 ,  F04D29/36 ,  G06F17/13 ,  G06F17/12 ,  G06F30/23

摘要： Conventional gas turbine engines are generally optimized to operate at nearly a fixed speed with fixed blade geometries for the design operating condition. When the operating condition of the engine changes, the flow incidence angles may not be optimum with the blade geometries resulting in reduced off-design performance. By contrast, according to embodiments of the present invention, articulating the pitch angle of turbine blades in coordination with adjustable nozzle vanes improves performance by maintaining flow incidence angles within the optimum range at all operating conditions of a gas turbine engine. Maintaining flow incidence angles within the optimum range can prevent the likelihood of flow separation in the blade passage and also reduce the thermal stresses developed due to aerothermal loads for variable speed gas turbine applications.