Compression system for a turbine engine

Patent metadata

Field	Value
Publication number	US-10294965-B2
Application number	US-201615163990-A
Country	US
Kind code	B2
Filing date	May 25, 2016
Priority date	May 25, 2016
Publication date	May 21, 2019
Grant date	May 21, 2019

Abstract

A blisk fan is provided for a turbine engine propulsion system. The blisk fan includes a hub configured to rotate about a rotational axis at a maximum rotational speed, and a plurality of blades extending radially outward from the hub to define a fan leading edge tip diameter. Each of the blades has a first vibratory mode at a natural frequency, which is greater than a first fan order and less than a second fan order at the maximum rotational speed. The compression system preferably has a balance factor of the compression system between 1.9 and 3.2.

First claim

What is claimed is:

1. A compression system for a turbine engine propulsion system comprising:
an axi-centrifugal compressor including an axial compressor section having a compressor inlet and a centrifugal compressor section having a compressor outlet;
a blisk fan positioned upstream of the axi-centrifugal compressor for directing at least a portion of a pressurized fluid stream to the compressor inlet, the blisk fan having a rotor hub configured to rotate about a rotational axis at a maximum rotational speed, and a plurality of blades materially joined with the rotor hub and extending radially outward from the rotor hub to define a fan leading edge tip diameter, wherein each of the plurality of blades has a first vibratory mode at a natural frequency which is greater than a first fan order and less than a second fan order at the maximum rotational speed; and
wherein a balance factor of the compression system is between 1.9 and 3.2.

2. The compression system according to claim 1 , wherein each of the plurality of blades intersects the rotor hub at a proximal end and extends radially from an inner root to an outer tip at a distal end and axially from a leading edge to a trailing edge, each of the plurality of blades comprising an airfoil having an aspect ratio not less than 1.2.

3. The compression system according to claim 2 , wherein the aspect ratio of each airfoil is not less than 1.5.

4. The compression system according to claim 1 , wherein the rotor hub comprises an annular portion providing an airflow surface between the plurality of blades, the airflow surface having a hub slope that is not less than 20 degrees with respect to the rotational axis.

5. The compression system according to claim 1 , wherein each of the plurality of blades intersects the rotor hub at a proximal end and extends radially from an inner root to an outer tip at a distal end such that a tangential tip speed of the outer tip is between 1300 ft/sec and 1550 ft/sec at the maximum rotational speed.

6. The compression system according to claim 1 , wherein each of the plurality of blades further comprises a first surface and a second surface opposite the first surface, and wherein the first vibratory mode comprises a first flexural mode flexing in a direction transverse to the first and second surfaces.

7. The compression system according to claim 1 , wherein the plurality of blades comprises at least a first set of blades having a first natural frequency for the first vibratory mode thereof and a second set of blades having a second natural frequency for the first vibratory mode thereof, wherein the second natural frequency is offset from the first natural frequency, wherein the first and second natural frequencies are greater than the first fan order and less than the second fan order at the maximum rotational speed.

8. The compression system according to claim 7 , wherein the number of blades in the first and second set of blades is equal and alternately distributed on the rotor hub.

9. The compression system according to claim 1 , wherein the fan leading edge tip diameter is not greater than 48 inches.

10. A propulsion system, comprising:
a turbine engine disposed in an engine cowl and operably coupled to a shaft assembly for rotation about a rotational axis, the turbine engine having an axi-centrifugal compressor including an axial compressor section having a compressor inlet and a centrifugal compressor section having a compressor outlet;
a fan section disposed in the engine cowl upstream of the axi-centrifugal compressor and operably coupled to the shaft assembly for drawing a fluid into the engine cowl and directing at least a portion of a pressurized fluid stream into the compressor inlet, the fan section including a rotor hub configured to rotate about the rotational axis at a maximum rotational speed, and a plurality of blades materially joined with the rotor hub and extending radially outward from the rotor hub to define a fan leading edge tip diameter, wherein each of the plurality of blades has a first vibratory mode at a natural frequency which is greater than a first fan order and less than a second fan order at the maximum rotational speed; and
wherein a balance factor of the fan section and axi-centrifugal compressor is between 1.9 and 3.2.

11. The propulsion system according to claim 10 wherein the fan leading edge tip diameter is not greater than 48 inches.

12. The propulsion system according to claim 10 , wherein each of the plurality of blades intersects the rotor hub at a proximal end and extends radially from an inner root to an outer tip at a distal end and axially from a leading edge to a trailing edge, each of the plurality of blades comprising an airfoil having an aspect ratio not less than 1.2.

13. The propulsion system according to claim 12 , wherein the aspect ratio of each airfoil is not less than 1.5.

14. The propulsion system according to claim 11 wherein the rotor hub comprises an annular portion providing an airflow surface between the plurality of blades, the airflow surface having a hub slope that is not less than 20 degrees with respect to the rotational axis.

15. The propulsion system according to claim 10 , wherein each of the plurality of blades intersects the rotor hub at a proximal end and extends radially from an inner root to an outer tip at a distal end such that a tangential tip speed of the outer tip is between 1300 ft/sec and 1550 ft/sec at the maximum rotational speed.

16. The propulsion system according to claim 10 , wherein each of the plurality of blades further comprises a first surface, a second surface opposite the first surface and the first vibratory mode comprises a first flexural mode flexing in a direction transverse to the first and second surfaces.

17. The propulsion system according to claim 10 , wherein the plurality of blades is divided into a first set of blades having a first natural frequency for the first vibratory mode thereof and a second set of blades having a second natural frequency for the first vibratory mode thereof, wherein the second natural frequency is offset from the first natural frequency, wherein the first and second natural frequencies are greater than the first fan order and less than the second fan order at the maximum rotational speed.

18. The propulsion system according to claim 16 , the number of blades in the first and second set of blades is equal and alternately distributed on the rotor hub.

19. The propulsion system according to claim 10 , further comprising a nose cone secured to the rotor hub upstream of the plurality of blades.

20. A propulsion system, comprising:
a turbine engine disposed in an engine cowl and operably coupled to a shaft assembly for rotation about a rotational axis, the turbine engine having an axi-centrifugal compressor including an axial compressor section having a compressor inlet and a centrifugal compressor section having a compressor outlet; and
a fan section disposed in the engine cowl upstream of the axi-centrifugal compressor and operably coupled to the shaft assembly for drawing a fluid into the engine cowl and directing at least a portion of a pressurized fluid stream into the compressor inlet, the fan section including a rotor hub configured to rotate about the rotational axis at a maximum rotational speed and having an annular portion, and a plurality of blades materially joined to the rotor hub, each blade intersecting the annular portion of the rotor hub at a proximal end to define an airflow surface having a hub slope th

Assignees

• Honeywell Int Inc

Inventors

• Nolcheff Nick
• Trego Michael Lamar
• Repp John
• Kroeger James

Classifications

• F05D2220/36

  specially adapted for the fan of turbofan engines · CPC title

• F04D19/02

  Multi-stage pumps · CPC title

• F04D29/666

  by means of rotor construction or layout, e.g. unequal distribution of blades or vanes · CPC title

• Y02T50/671

  Cross-Sectional Technologies · mapped topic

• F04D19/002

  Axial flow fans · CPC title