Back to results
US 12,595,907 B2Granted
Inspection port for an attritable engine support structure
AssigneeRtx Corporation
InventorsLawrence A. Binek, Evan J. Butcher, Sean R. Jackson
Life of this patent
Estimating the term…
Abstract
A gas turbine engine includes an engine casing and a combustor liner enclosed within the engine casing. The engine includes a flow path for cooling the combustor liner with an air stream and located in between the engine casing and the combustor liner. The engine includes an inspection port penetrating the engine casing, the flow path, and the combustor liner and wherein the inspection port is positioned to allow an operator to view sacrificed zones of a sacrificial support structure.
Claims19
A gas turbine engine comprising:
- an engine casing;
- a combustor liner enclosed within the engine casing;
- a flow path for cooling the combustor liner with an air stream and located in between the engine casing and the combustor liner;
- a dilution chute projecting out from the combustor liner;
- a support structure extending between the combustor liner and the dilution chute, the support structure configured to support the dilution chute during manufacturing where the support structure is additively manufactured with the combustor liner and the dilution chute as a unitized body;
- and
- an inspection port penetrating the engine casing, the flow path, and the combustor liner, the inspection port positioned to allow an operator to view a zone of the support structure;
- wherein the inspection port is circumferentially adjacent an ignitor such that the inspection port and an ignitor inlet for the ignitor penetrate through a common section of the combustion liner.
5 more elements
A gas turbine engine comprising:
- an engine casing;
- a combustor liner enclosed within the engine casing;
- a flow path for cooling the combustor liner with an air stream and located in between the engine casing and the combustor liner;
- a dilution chute penetrating the combustor liner;
- a sacrificial support structure attached to the dilution chute and the combustor liner;
- and
- an inspection port penetrating the engine casing, the flow path, and the combustor liner, the inspection port positioned to allow an operator to view a portion of the sacrificial support structure, the inspection port formed by a sidewall that projects out from the combustor liner and through the engine casing, and the sidewall is formed integral with the combustor liner;
- wherein an outer surface of the sidewall extends longitudinally from the engine casing to the combustor liner, and the outer surface has a straight sectional geometry from the engine casing to the combustor liner.
5 more elements
A gas turbine engine, comprising:
- an engine casing;
- a combustor liner within the engine casing;
- a dilution chute projecting out from the combustor liner into a combustion chamber;
- a support structure connected to and extending between the combustor liner and the dilution chute;
- and
- an inspection port extending through the engine casing and the combustor liner to the combustion chamber, the inspection port formed by a sidewall connected to the combustor liner, and the sidewall extending across a cavity that is formed by and that extends between the combustor liner and the engine casing;
- wherein an outer surface of the sidewall has a straight sectional geometry as the sidewall extends across the cavity from the engine casing to the combustor liner.
4 more elements
Dependencies are inferred from the claim text.