Rolls-royce North American Technologies Inc.

Rolls-royce Corporation

Mark O'Leary

Daniel Kent Vetters

Ted Joseph Freeman

Matthew R Brandt

David Levi Sutterfield

Nathan Ottow

Christopher J Bies

An instrumentation assembly configured to measure properties of an engine exhaust stream is disclosed in this paper. The instrumentation assembly may include an outer support ring that extends around a central axis, an inner support ring arranged radially inward of the outer support ring around the central axis, and a plurality of instrumentation rake assemblies. The plurality of instrumentation rake assemblies extends from the outer support ring to the inner support ring across an annular passageway defined between the outer support ring and the inner support ring configured to carry the engine exhaust stream.

Engine-mounted instrumentation assembly

Dynamic instrumentation assembly to measure properties of an engine exhaust stream

A turbine shroud adapted for use in a gas turbine engine includes a plurality of metallic carrier segments and a plurality of blade track segments mounted to corresponding metallic carrier segments. Cooling air is directed onto the blade track segments to cool the blade track segments when exposed to high temperatures in a gas turbine engine.

Turbine shroud segment with flange-facing perimeter seal

A coupling adapted for use with a gas turbine engine includes a first flange, a second flange, and a seal assembly. The first flange is coupled with an exhaust end of the gas turbine engine. The second flange is coupled with ducting downstream of the gas turbine engine. The seal assembly extends between the first flange and the second flange and is configured to block the gases from passing radially between the first flange and the second flange.

Flexible seal for gas turbine engine

A turbine shroud segment of a turbine shroud for use in a turbine of a gas turbine engine is disclosed herein. The turbine shroud segment includes a carrier segment and a blade track segment. The carrier segment includes metallic materials. The blade track segment includes ceramic matrix composite materials. A seal is arranged between the carrier segment and the blade track segment.

Turbine shroud segment with side perimeter seal

Turbine shroud segment with load distribution springs

A method of manufacturing a gas turbine engine component and the resulting component configuration are disclosed. The method includes providing a ceramic structure including a sacrificial ceramic core. The ceramic structure is inserted into a casting mold. A component material is introduced into the casting mold. The ceramic structure is removed after the component material has solidified to define a casted component having a cooling cavity of a heat exchanger segment formed in the wall structure of the component. The ceramic body of the sacrificial ceramic core defines a plurality of apertures and includes a trailing first pin and a leading first pin. The trailing first pin and the leading first pin are extended away from an inner surface of the body, and the leading first pin is spaced from the trailing first pin and in closer proximity to a leading edge of the body than the trailing first pin.

Gas engine component with cooling passages in wall and method of making the same

Turbine shroud segment with buffer air seal system

An airfoil adapted for use in a gas turbine engine is disclosed herein. The airfoil includes a spar defining an interior space and a cover sheet extending around at least a portion of the spar. The cover sheet is bonded to the spar to define a cooling cavity between the spar and the cover sheet.

Dual wall airfoil with stiffened trailing edge

A ceramic structure may include a sacrificial ceramic core. The sacrificial ceramic core may include a ceramic body corresponding to a cooling cavity of a heat exchanger segment. The ceramic body may have an exterior surface that includes an outer surface and an inner surface interconnected to one another by at least a leading edge, a trailing edge, a tip facing edge and a base facing edge. The ceramic body may define a plurality of apertures extending between the outer surface and the inner surface. The ceramic body may include a trailing first pin and a leading first pin. The trailing first pin and the leading first pin may extend away from the inner surface. The leading first pin may be spaced away from the trailing first pin and in closer proximity to the leading edge than the trailing first pin.

Gas engine component with cooling passages in wall

Various embodiments of the present disclosure provide an aircraft anti-icing system that includes an aircraft engine inlet component, a pressurized air source, and a heat source operable to: (1) heat the leading edge of the aircraft engine inlet component via the heat source to prevent ice formation on the outer surface of the leading edge; and (2) direct pressurized air from the pressurized air source so that it forces water off of the outer surface of the inlet components (and into the external air flow) as the water travels downstream from the leading edge outer surface downstream toward the trailing edge, which prevents runback ice formation.

Aircraft anti-icing system

A turbine shroud adapted to extend around a bladed turbine wheel to block gasses from passing over the bladed turbine wheel is disclosed. In a segmented embodiment, each turbine shroud segment may include a carrier segment and a blade track segment. The carrier segment may comprise metallic materials and may be formed to define an attachment-receiving space. The blade track segment may comprise ceramic matrix composite materials and may be formed to include an attachment portion that extends radially outward from the runner into the attachment-receiving space formed by the carrier segment.

Growing community of inventors

Zionsville, IN, United States of America

Mark O'Leary