公开(公告)号：US20170107830A1

公开(公告)日：2017-04-20

申请号：US14886201

申请日：2015-10-19

Applicant: United Technologies Corporation

Inventor： Joseph F. Englehart ,  Edward F. Pietraszkiewicz ,  Wieslaw A. Chlus ,  David M. Konopka ,  Luke A. Hmiel ,  Kenneth Boucher

IPC: F01D5/18 ,  F02C3/04 ,  F02C7/18 ,  F01D5/14

Abstract: A blade assembly includes a blade and a blade platform secured to the blade. The blade extends radially from the blade platform. The blade platform includes at least one platform airflow passage located therein. A gusset extends from the blade to the blade platform. The gusset includes a gusset airflow passage fluidly connected to the platform airflow passage to convey an airflow to the platform airflow passage. a gas turbine engine includes a combustor and a plurality of gas turbine engine components located in fluid communication with the combustor. The gas turbine engine component includes an airfoil portion and a platform secured to the airfoil portion. The platform includes at least one platform airflow passage positioned therein. A gusset extends from the airfoil portion to the platform. The gusset includes a gusset airflow passage fluidly connected to the platform airflow passage to convey an airflow to the platform airflow passage.

公开(公告)号：US10677070B2

公开(公告)日：2020-06-09

申请号：US14886201

申请日：2015-10-19

Applicant: United Technologies Corporation

Inventor： Joseph F. Englehart ,  Edward F. Pietraszkiewicz ,  Wieslaw A. Chlus ,  David M. Konopka ,  Luke A. Hmiel ,  Kenneth Boucher

IPC: F02C1/00 ,  F01D5/18 ,  F01D5/14 ,  F02C3/04 ,  F02C7/18

Abstract: A blade assembly includes a blade and a blade platform secured to the blade. The blade extends radially from the blade platform. The blade platform includes at least one platform airflow passage located therein. A gusset extends from the blade to the blade platform. The gusset includes a gusset airflow passage fluidly connected to the platform airflow passage to convey an airflow to the platform airflow passage. a gas turbine engine includes a combustor and a plurality of gas turbine engine components located in fluid communication with the combustor. The gas turbine engine component includes an airfoil portion and a platform secured to the airfoil portion. The platform includes at least one platform airflow passage positioned therein. A gusset extends from the airfoil portion to the platform. The gusset includes a gusset airflow passage fluidly connected to the platform airflow passage to convey an airflow to the platform airflow passage.