United Technologies Corporation

Raytheon Technologies Corporation

Di Wu

Brandon W Spangler

Edwin Otero

Daniel A Snyder

Timothy Charles Nash

Jaimie Schweitzer

Jaimie Taraskevich

A turbomachine airfoil element comprises an airfoil having: an inboard end; an outboard end; a leading edge; a trailing edge; a pressure side; and a suction side. A span between the inboard end and the outboard end is 1.35-1.65 inches. A chord length at 50% span is 1.20-1.60 inches. At least two of: a first mode resonance frequency is 2858&#xb1;10% Hz; a second mode resonance frequency is 4916&#xb1;10% Hz; a third mode resonance frequency is 7160&#xb1;10% Hz; a fourth mode resonance frequency is 10268&#xb1;10% Hz; a fifth mode resonance frequency is 14235&#xb1;10% Hz; and a sixth mode resonance frequency is 15088&#xb1;10% Hz.

Turbomachine blade

In various embodiments, an airfoil used as a turbine blade for a turbine wheel in a gas turbine engine is provided. The airfoil may comprise a root, a tip, and a body. The root may have a first area. The tip may have a second area. The body may have a chord bounded by the root and the tip. The body may also define a cooling chamber. The cooling chamber may have a first rib substantially perpendicular to the chord. The cooling chamber may also have a second rib extending partially between the root and the tip.

Airfoil support and cooling scheme

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West Hartford, CT, United States of America

Di Wu