Honeywell International Inc.

Alliedsignal Inc.

Ronald B Pardington

Paul Yankowich

Frank Joseph Zupanc

Rodolphe Dudebout

Cristopher Frost

Nagaraja S Rudrapatna

Hans Heydrich

Jurgen C Schumacher

Daih-Yeou Chen

Thomas Frank Johnson

Jonathan N Kettinger

In accordance with an exemplary embodiment, a fuel injector assembly is provided for a gas turbine engine with a compressor section and a combustion section. The fuel injector assembly includes a stem defining a fuel path for fuel and a flow guide coupled to and extending along the stem. The flow guide receives an air flow. The assembly further includes a swirler apparatus coupled to the stem and configured to receive the fuel. The swirler apparatus is further coupled to the flow guide and configured to receive the air flow. The swirler apparatus is configured to mix the fuel and the air flow and direct the mixture into a combustor of the combustor assembly.

Gas turbine fuel injector having flow guide for receiving air flow

A combustor dome and heat-shield assembly comprises a heat-shield having a first opening therethrough. A swirler extends through the first opening and captures the heat-shield. A dome having a second opening therethrough and has an upstream side and a downstream side. The swirler extends through the second opening from the downstream side to the upstream side to capture the heat-shield on the downstream side, and a retaining clip engages the swirler to secure the swirler and the heat-shield on the dome.

Combustor dome and heat-shield assembly

A combustor liner assembly includes a liner and a first group of cooling holes formed in the liner and having an increasing density in a downstream direction. The first group of cooling holes include a generally circumferential first row of cooling holes, a generally circumferential second row of cooling holes immediately downstream from, consecutive to, and separated from the first row at a first distance, a generally circumferential third row of cooling holes immediately downstream from, consecutive to, and separated from the second row at a second distance, and a generally circumferential fourth row of cooling holes immediately downstream from, consecutive to, and separated from the third row at a third distance. The first distance is greater than the second distance and the third distance, and the second distance is greater than the third distance.

Combustor systems with liners having improved cooling hole patterns

A retaining ring is provided for use in conjunction with a carburetor assembly having a flow passage therethrough for conducting a fuel-air mixture into a combustion chamber, the carburetor assembly comprising an air flow modifier and a fuel injector receiving element adjacent thereto. The retaining ring comprises a collar configured to engage the fuel injector receiving element so as to maintain its position adjacent the air flow modifier, and a retaining portion coupled to the collar and configured to engage the air flow modifier to secure the airflow modifier to the combustion chamber. The retaining portion cooperates with the collar to form an aperture through the retaining ring for receiving the carburetor assembly.

Combustor dome assembly including retaining ring

A turbine engine is disclosed that is capable of operating in an emergency power mode, an air breathing auxiliary power mode and a bypass bleed environmental control mode. In a preferred embodiment of the invention, the engine comprises in working fluid flow order a compressor for compressing air, a combustion chamber and a power turbine for extracting mechanical work from heated and/or compressed air. The compressor and turbine are separately coupled by a shaft which is also coupled to a generator for supplying electrical power and a cooling turbine for supplying cooled air to the aircraft cabin and avionics. The combustion chamber has an upstream combustor inlet and a downstream combustor inlet, each of which may admit compressed air either to be mixed with fuel for combustion, or to pass directly to the combustor outlet which is operatively attached to the power turbine section inlet. During emergency/starting operation, the combustion chamber and turbine section receive compressed air from a stored air accumulator through a stored air inlet. During normal air breathing operation, the combustion chamber and turbine section receive compressed air from a compressor through an air breathing inlet. During bypass bleed operation, the combustion chamber and turbine section receive compressed air from the aircraft main engine through a bypass bleed air inlet. The tri-mode operation is made possible by a unique two-way bypass ring having a plurality of axial passages communicating the stored air inlet and air breathing inlet with the upstream combustor inlet and a plurality of radial passages communicating the bypass bleed inlet with the downstream combustor inlet. A valving system selectively admits compressed air into the combustor and turbine section from the stored air inlet, air breathing inlet or bypass bleed inlet depending on the mode of operation.

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Gilbert, AZ, United States of America

Ronald B Pardington