Gas turbine engine flow path geometry

Number of patents in Portfolio can not be more than 2000

United States of America Patent

PATENT NO 9568009
APP PUB NO 20150128604A1
SERIAL NO

14092356

Stats

ATTORNEY / AGENT: (SPONSORED)

Importance

Loading Importance Indicators... loading....

Abstract

See full text

A flow path surface of a gas turbine engine at the location of a bladed component is disclosed in which the flow path surface includes a cylindrical upstream side and a conical downstream side. The bladed component is located at the intersection of the cylindrical upstream side and the conical downstream side. The cylindrical upstream side can extend from a leading edge of the bladed component, or a point upstream of it, to a location between the leading edge and trailing edge of the component. The conical downstream side can extend past the trailing edge of the bladed component. The bladed component can be a fan blade or a compressor blade.

Loading the Abstract Image... loading....

First Claim

See full text

Family

Loading Family data... loading....

Patent Owner(s)

  • ROLLS-ROYCE CORPORATION

International Classification(s)

Inventor(s)

Inventor Name Address # of filed Patents Total Citations
Fulayter, Roy D Avon, US 13 140
Power, Bronwyn Brownsburg, US 15 28
Rivers, Jonathan M Indianapolis, US 20 50

Cited Art Landscape

Load Citation

Patent Citation Ranking

Forward Cite Landscape

Load Citation

Maintenance Fees

Fee Large entity fee small entity fee micro entity fee due date
11.5 Year Payment $7400.00 $3700.00 $1850.00 Aug 14, 2028
Fee Large entity fee small entity fee micro entity fee
Surcharge - 11.5 year - Late payment within 6 months $160.00 $80.00 $40.00
Surcharge after expiration - Late payment is unavoidable $700.00 $350.00 $175.00
Surcharge after expiration - Late payment is unintentional $1,640.00 $820.00 $410.00