Raytheon Technologies Corporation

United Technologies Corporation

Rtx Corporation

Sean Nolan

William R Edwards

Charles H Warner

Yuan Dong

Eliannah Hunderfund

Haiyun Li

Ernest D Casparie

Mark David Ring

Simon W Evans

Robert W Fessenden

Li Xing Pan

John P Virtue

Sue-Li Chuang

Rishon Saftler

Matthew R Willett

Stephen A Sarcich

Joseph Steele

Abhir A Adhate

Brian Green

Crystal Monteiro

Brittany Travis

Marian A Iskandar

Sue-Li Kingsley Chuang

A compressor section for a gas turbine engine includes a blade including a platform, a tip and an airfoil extending between the platform and tip. The airfoil includes a root portion adjacent to the platform, a midspan portion and a tip portion. Each of the root portion, midspan portion and tip portion define a meridional velocity at stage exit with the tip portion including a first meridional velocity greater than a second meridional velocity of the midspan portion. A blade for an axial compressor of a gas turbine engine and a method of operating a compressor section of a gas turbine engine are also disclosed.

Repeating airfoil tip strong pressure profile

A turbomachine airfoil element includes an airfoil having 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 0.83-0.93 inch (21.1-23.6 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 0.80-0.90 inch (20.4-22.9 mm). The airfoil element includes at least two of a first mode with a frequency is 3135&#xb1;10% Hz, a second mode with a frequency is 6634&#xb1;10% Hz, a third mode with a frequency is 13260&#xb1;10% Hz, a fourth mode with a frequency is 16838&#xb1;10% Hz and a fifth mode with a frequency is 17980&#xb1;10% Hz.

Gas turbine engine airfoil frequency design

A turbomachine airfoil element includes an airfoil having 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 0.60-0.70 inch (15.3-17.8 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 0.90-1.00 inch (22.9-25.5 mm). The airfoil element includes at least two of a first mode with a frequency of 5327&#xb1;10% Hz, a second mode with a frequency of 8393&#xb1;10% Hz, a third mode with a frequency of 16289&#xb1;10% Hz, a fourth mode with a frequency of 25049&#xb1;10% Hz and a fifth mode with a frequency of 27423&#xb1;10% Hz.

A turbomachine airfoil element includes an airfoil having 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 0.70-0.85 inch (17.8-20.3 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 0.85-0.95 inch (21.5-24.0 mm). The airfoil element includes at least two of a first mode with a frequency of 4508&#xb1;10% Hz, a second mode with a frequency of 7466&#xb1;10% Hz, a third mode with a frequency of 16104&#xb1;10% Hz, a fourth mode with a frequency of 18397&#xb1;10% Hz and a fifth mode with a frequency of 20855&#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 0.55-0.65 inch (14.0-16.5 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 0.76-0.86 inch (19.3-21.8 mm). The airfoil element includes at least two of a first mode with a frequency of 3335&#xb1;10% Hz, a second mode with a frequency of 5715&#xb1;10% Hz and a third mode with a frequency of 41797&#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 1.13-1.23 inch (28.7-31.2 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 0.64-0.74 inch (16.3-18.8 mm). The airfoil element includes at least two of a first mode with a frequency of 1634&#xb1;10% Hz, a second mode with a frequency of 5611&#xb1;10% Hz, a third mode with a frequency of 19027&#xb1;10% Hz, a fourth mode with a frequency of 29268&#xb1;10% Hz, a fifth mode with a frequency of 33103&#xb1;10% Hz, a sixth mode with a frequency of 34908&#xb1;10% Hz and a seventh mode with a frequency of 41277&#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 1.03-1.13 inch (26.2-28.7 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 0.93-1.03 inch (23.6-26.2 mm). The airfoil element includes at least two of a first mode with a frequency of 2182&#xb1;10% Hz, a second mode with a frequency of 4966&#xb1;10% Hz, a third mode with a frequency of 9675&#xb1;10% Hz, a fourth mode with a frequency of 13154&#xb1;10% Hz and a fifth mode with a frequency of 14056&#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 0.63-0.73 inch (16.0-18.5 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 0.61-0.71 inch (15.5-18.0 mm). The airfoil element includes at least two of a first mode with a frequency of 4852&#xb1;10% Hz, a second mode with a frequency of 11917&#xb1;10% Hz, a third mode with a frequency of 30842&#xb1;10% Hz and a fourth mode with a frequency of 35225&#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 0.75-0.85 inch (19.1-21.6 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 0.56-0.66 inch (14.2-16.8 mm). The airfoil element includes at least two of a first mode with a frequency of 2740&#xb1;10% Hz, a second mode with a frequency of 5956&#xb1;10% Hz, a third mode with a frequency of 6554&#xb1;10% Hz and a fourth mode with a frequency of 31959&#xb1;10% Hz.

Rotor of a gas turbine engines having a rotor hub and a plurality of blades extending from the rotor hub, wherein each blade has a full-span forward sweep along a leading edge of the blade that starts at an airfoil root of the blade at the hub and extends to a blade tip, wherein a sweep of a blade is a percentage of a root axial chord length of the respective blade.

Full-span forward swept airfoils for gas turbine engines

A compressor may include an airfoil configured to rotate about an axis. The airfoil may have a span measured radially from a root of the airfoil to a tip of the airfoil. A compressor case may be radially adjacent to the airfoil. The airfoil and the compressor case may define a clearance between the tip of the airfoil and a radially inner surface of the compressor case. A ratio of the clearance to the span may be between 1.5 to 2.5 percent.

Gas turbine engine airfoil

A disclosed gas turbine engine includes a case for a case for a compressor section including a bleed air slot. The bleed air slot includes an inlet having a first area radially inward of an outlet having a second area with the second area being greater than the first area. The bleed air slot further includes a center portion disposed along a radial line extending from an axis of the engine and an elongated portion extending from the opening at an angle relative to a line normal to the radial line.

Bleed air slot

An airfoil comprises pressure and suction surfaces extending axially from a leading edge to a trailing edge and radially from a root section to a tip section, defining a mean span therebetween. An inner endwall defines an inner endwall contour extending axially and circumferentially from the root section, and an outer endwall defines an outer endwall contour extending axially and circumferentially from the tip section. The inner and outer endwall contours are defined by varying radial deviations from circumferentially uniform nominal inner and outer radii, where one of the radial deviations varies axially and circumferentially by at least three percent of a mean span of the airfoil.

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Wethersfield, CT, United States of America

Sean Nolan