United Technologies Corporation

Dennis J Sullivan

James A Dierberger

Aaron S Butler

Masamichi Hongoh

Mark A Kelley

Thomas J Madden

Theodore G Fox

Robert W Soderquist

Jason S Pettengill

George A Lanati

Vernon A Goodrich

John S Thackrah

A combustor for a gas turbine engine includes an interface shield between a first heat shield and a second heat shield.

Interface heat shield for a combustor of a gas turbine engine

A combustor of a gas turbine engine includes a heat shield panel mounted to a support shell and an insert at least partially between opposed surfaces of the support shell and the heat shield panel, the insert exposed to a combustion chamber, and the insert being flush with a hot side of the heat shield.

Insert adjacent to a heat shield element for a gas turbine engine combustor

A combustor for a gas turbine engine is provided that includes a support shell, a forward liner segment, an aft liner segment, and a seal member. The support shell has an interior surface, and exterior surface, and a plurality of impingement apertures disposed within the shell. The forward liner segment and aft liner segment are attached to the inner surface of the shell. The forward liner segment has an edge surface extending between a face surface and a back surface, and a seal shoulder. The aft liner segment has an edge surface extending between a face surface and a back surface, and a seal shoulder. The forward liner segment and the aft liner segment are separated from one another by a gap. The seal member is disposed within the gap. At least some of the plurality of impingement apertures disposed within the shell are aligned with the seal member and oriented to direct cooling air to impinge on the seal member.

Combustor liner segment seal member

A combustor liner segment seal member is provided that includes a center section, a forward flange, and an aft flange. The center section includes a base surface, a gas path surface, a forward side surface, and an aft side surface. The forward flange extends outwardly from the forward side surface, and includes a width, a height, a shell side surface, and a liner side surface. The aft flange extends outwardly from the aft side surface, and includes a width, a height, a shell side surface, and a liner side surface.

A premixing fuel injector for a turbine engine includes easily replaceable means for monitoring temperature or other conditions of interest in the interior of the injector. The fuel injector includes a guide conduit (70) that penetrates into the injector's interior and has an externally accessible opening (74) for receiving a sensor probe (88). The probe carries at least one sensor, such as a thermocouple junction (106), for monitoring temperature or other conditions inside the injector. In one embodiment, the guide conduit has a nonlinear shape and the probe shank (92) is sufficiently flexible to follow the contour of the conduit and sufficiently rigid to overcome any insertion resistance that the conduit might offer. The flexibility of the shank (92) may vary longitudinally to enhance insertability of the probe into the conduit. The probe is longitudinally oversized relative to the conduit so that when the probe is correctly installed, a sensor element positioned at the probe tip (93) contacts the closed, distal end (84) of the conduit to improve the sensor's responsiveness to changing conditions inside the injector. The probe shank may also buckle slightly and press against the internal sidewall of the conduit to prevent excessive shank vibration.

Fuel injector with a replaceable sensor

A support structure for a low NO.sub.x industrial gas turbine engine fuel nozzle includes a pressure vessel which forms an interior cavity such that the exterior of the pressure vessel is exposed to the high pressure and temperature of the compressor outlet while the interior cavity of the pressure vessel is exposed to ambient conditions. The fuel lines to the nozzle run through the interior cavity of the pressure vessel, isolated from the high temperatures and pressures at the compressor outlet. The pressure vessel housing and the ambient air within the housing act as natural insulators which prevent the fuel lines from becoming too hot and coking. The support structure also facilitates maintenance of the combustor section of the engine since the low NO.sub.x fuel nozzle and the annular combustor assembly of the engine are easily accessible for maintenance.

Pressure vessel fuel nozzle support for an industrial gas turbine engine

When second shell section 18 diverges with respect to first shell section 16, the second liner panel 50 is located with a changing spacing from the shell. The liner is close to the shell at the upstream edge 68, and farther from the liner at the downstream end 57. The downstream end of the first liner panel 64 overlaps the second liner panel 50 on the gas side.

Gas turbine engine combustion liner float wall cooling arrangement

A deflector assembly (20) includes an annular plate portion (28) with pairs of parallel substantially radial slots (30). Truncated pie shaped segments (34) are secured (32, 36) to the plate with cooling air (40, 52) directed between the segments and the plate. Extended cooling surface (48) increases the cooling effect of the airflow. The segments are free from thermal fight and direct the discharged cooling air to help cool the remaining exposed bulkhead surface or shield.

Combustor segmented deflector

The turbine vanes of a gas turbine engine immediately downstream of the combustor are maintained at a cool temperature by judiciously directing cooling air at the stagnation point ahead of the vane's leading edge at the juncture of the vane's airfoil section and platform.

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Vernon, CT, United States of America

Dennis J Sullivan