Invention Grant
- Patent Title: Efficient, low pressure ratio propulsor for gas turbine engines
-
Application No.: US14695373Application Date: 2015-04-24
-
Publication No.: US09909505B2Publication Date: 2018-03-06
- Inventor: Edward J. Gallagher , Byron R. Monzon , Shari L. Bugaj
- Applicant: United Technologies Corporation
- Applicant Address: US CT Farmington
- Assignee: United Technologies Corporation
- Current Assignee: United Technologies Corporation
- Current Assignee Address: US CT Farmington
- Agency: Carlson, Gaskey & Olds, P.C.
- Main IPC: F02C7/36
- IPC: F02C7/36 ; F02K1/06 ; F02K3/06 ; F01D5/28 ; F01D5/14 ; F01D15/12 ; F04D29/02 ; F04D29/053 ; F04D29/32 ; F04D29/38 ; F04D29/52 ; F04D29/56
Abstract:
A gas turbine engine includes a core flow passage, a bypass flow passage, and a propulsor arranged at an inlet of the bypass flow passage and the core flow passage. The propulsor includes a row of propulsor blades. The row includes no more than 20 of the propulsor blades. The propulsor has a pressure ratio between about 1.2 and about 1.7 across the propulsor blades.
Public/Granted literature
- US20160201607A1 EFFICIENT, LOW PRESSURE RATIO PROPULSOR FOR GAS TURBINE ENGINES Public/Granted day:2016-07-14
Information query
IPC分类:
