Raytheon Technologies Corporation

United Technologies Corporation

Rtx Corporation

Konstantinos Panagiotis Giannakopoulos

Xuedong Zhou

Christopher B Jelks

Kate Hudon

Mark David Ring

Kurt R Heinemann

John Joseph Papalia

Sumin Tao

Matthew E Bintz

Joseph C Straccia

Joseph Wieser

Evan K Fink

Jashandeep Singh

Thomas E Clark

Jeffrey T Morton

Murat Yazici

Joon Ha

Scott C Billings

Robert B Fuller

Zhen Wu

Erica J Harvie

William W Frank

Michael C Weber

Andrew C Carmack

Mohammad G Faisal

Thomas Carlsen

Bill Nguyen

Alexei T Marqueen

An assembly is provided for an aircraft propulsion system. This assembly includes an open propulsor rotor and an open guide vane structure. The open propulsor rotor is configured to rotate about a rotational axis. The open guide vane structure is axially next to the open propulsor rotor. The open guide vane structure includes a plurality of open guide vanes arranged circumferentially about the rotational axis. The open guide vanes include a first open guide vane. The first open guide vane includes a first vane leading edge, a first vane trailing edge and a fixed first vane chord length measured from the first vane leading edge to the first vane trailing edge. The first open guide vane is configured to translate axially along the rotational axis.

Translatable guide vanes for aircraft propulsion system

An anti-vortex tube (AVT) retaining ring and bore basket is provided and includes a unitary body having an inboard portion, an outboard portion and an intermediate portion. The inboard portion includes a first ring-shaped body with an outer diameter. The outboard portion is configured to support an array of AVTs and includes a second ring-shaped body with an inner diameter larger than the outer diameter of the first ring-shaped body. The intermediate portion includes a flange extending between the outer and inner diameters of the first and second ring-shaped bodies, respectively.

Anti-vortex tube retaining ring and bore basket

A flange includes a flange body and a scallop feature. The flange body is annularly disposed about a longitudinal axis. The flange body includes a first radial side and a second radial side radially opposite the first radial side. The flange body defines a first fastener hole and a circumferentially adjacent second fastener hole. Each of the first fastener hole and the second fastener hole are formed through the flange body. The scallop feature is formed through the flange body and disposed circumferentially between the first and second fastener holes. The scallop feature extends radially from the first radial side through at least a portion of the flange body. The scallop feature includes a first side and a second side, parallel to the first side.

Case flange with scallop features

A case assembly for a gas turbine engine includes a case extending circumferentially about an engine central longitudinal axis and two or more components installed in the case at different axial and/or radial locations. A retainer is installed at a circumferential end of the case, the retainer configured to circumferentially retain the two or more components at the case. A circumferential retainer of a case assembly of a gas turbine engine includes a retainer pin configured for installation in retaining feature of a circumferential end of a case, and one or more retainer arms extending from the retainer pin. The one or more retainer arms are configured to extend at least partially across two or more components installed in the case at different axial and/or radial locations to circumferentially retain the two or more components at the case.

Multi-purpose anti-rotation lock pin

A turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 4.47-4.77 inch (113.5-121.2 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span and is in a range of 2.57-2.87 inch (65.3-72.9 mm). The airfoil element includes at least two of a first mode with a frequency of 297&#xb1;10% Hz, a second mode with a frequency of 1035&#xb1;10% Hz, a third mode with a frequency of 1488&#xb1;10% Hz, a fourth mode with a frequency of 1524&#xb1;10% Hz, a fifth mode with a frequency of 2855&#xb1;10% Hz and a sixth mode with a frequency of 4462&#xb1;10% Hz.

Gas turbine engine airfoil frequency design

A borescope plug system includes a housing, a driver, and a spring. The housing includes a first housing end and a second housing end. The housing further includes a longitudinally extending centerline extending between the first housing end and the second housing end. The driver is disposed at least partially within the housing along the longitudinally extending centerline and includes a first driver end and a second driver end. The spring is disposed within the housing and couples the housing to the driver. The driver is configured to move within the housing, along the longitudinally extending centerline, to engage the first driver end with a borescope plug of a borescope plug port, and to install or remove the borescope plug from the borescope plug port based on a rotation of the driver about the longitudinally extending centerline.

Borescope plug system

An apparatus is provided that includes a rotor bore and a bore basket. The bore basket extends axially between a first and second axial ends. The bore basket includes an engagement panel, and cylindrical inner and outer radial panels. The inner and outer radial panels extend substantially between the first and second axial ends. The inner radial panel is disposed radially inside of and separated from the outer radial panel, defining an annular passage disposed there between. The bore basket includes a plurality of inlet apertures in fluid communication with the annular passage at a first axial position, and a plurality of exit apertures in fluid communication with the annular passage at a second axial position. The second axial end of the bore basket is attached to an inner radial hub of the rotor bore, and the rotor bore and bore basket are a unitary structure.

Integral rotor bore and bore basket

A turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 3.68-3.98 inch (93.5-101.1 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span is in a range of 1.75-2.05 inch (44.5-52.1 mm). The airfoil element includes at least two of a first mode with a frequency of 436&#xb1;10% Hz, a second mode with a frequency of 1557&#xb1;10% Hz, a third mode with a frequency of 1424&#xb1;10% Hz, a fourth mode with a frequency of 1870&#xb1;10% Hz, a fifth mode with a frequency of 3321&#xb1;10% Hz and a sixth mode with a frequency of 3957&#xb1;10% Hz.

A turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 2.99-3.29 inch (75.9-83.6 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span and is in a range of 1.44-1.74 inch (36.6-44.2 mm). The airfoil element includes at least two of a first mode with a frequency of 430&#xb1;10% Hz, a second mode with a frequency of 1459&#xb1;10% Hz, a third mode with a frequency of 2036&#xb1;10% Hz, a fourth mode with a frequency of 3615&#xb1;10% Hz, a fifth mode with a frequency of 4722&#xb1;10% Hz and a sixth mode with a frequency of 5591&#xb1;10% Hz.

A turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 4.35-4.65 inch (110.5-118.1 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span and is in a range of 2.45-2.75 inch (62.2-69.9 mm). The airfoil element includes at least two of a first mode with a frequency of 255&#xb1;10% Hz, a second mode with a frequency of 818&#xb1;10% Hz, a third mode with a frequency of 1439&#xb1;10% Hz, a fourth mode with a frequency of 2035&#xb1;10% Hz, a fifth mode with a frequency of 3033&#xb1;10% Hz and a sixth mode with a frequency of 3740&#xb1;10% Hz.

A compressor rotor includes a first disk and a conical section connected to the first disk. The conical section includes at least one flow hole. A bore cavity is defined between the conical section and the first disk. The bore cavity is arranged in fluid communication with the at least one flow hole. An anti-vortex tube is disposed within the at least one flow hole of the conical section and includes at least one feature arranged in contact with a surface of the conical section to restrict movement of the anti-vortex tube out of engagement with the conical section.

Flared anti-vortex tube rotor insert

A turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 3.45-3.75 inch (87.6-95.3 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span and is in a range of 1.55-1.85 inch (39.4-47.0 mm). The airfoil element includes at least two of a first mode with a frequency of 424&#xb1;10% Hz, a second mode with a frequency of 1401&#xb1;10% Hz, a third mode with a frequency of 1770&#xb1;10% Hz, a fourth mode with a frequency of 3336&#xb1;10% Hz, a fifth mode with a frequency of 3378&#xb1;10% Hz and a sixth mode with a frequency of 4141&#xb1;10% Hz.

A bore basket assembly for a gas turbine engine. The assembly includes an outer cylindrical member. The assembly also includes an inner cylindrical member at least partially surrounded by the outer cylindrical member to define an annulus therebetween, one of the cylindrical members operatively coupled to an aft rotor stage, the other of the cylindrical members operatively coupled to a forward rotor stage, the cylindrical members moveable in an axially telescoping manner relative to each other.

Telescoping bore basket for gas turbine engine

A high pressure compressor rotor stack includes a bore basket that includes a bore basket internal passage. A first plurality of rotor stages at least partially defines a forward rotor bore with a forward hub structure and the bore basket. A second plurality of rotor stages at least partially defines an aft rotor bore with an aft hub structure and the bore basket.

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Middletown, CT, United States of America

Konstantinos Panagiotis Giannakopoulos