Turbine engine with a swirler

Patent metadata

Field	Value
Publication number	US-11060405-B2
Application number	US-201716098515-A
Country	US
Kind code	B2
Filing date	May 18, 2017
Priority date	May 25, 2016
Publication date	Jul 13, 2021
Grant date	Jul 13, 2021

Abstract

An apparatus and method for a turbine engine including an engine core having a compressor section, a combustor, and a turbine section, which are arranged to define a stator and rotor. The engine further includes a swirler to increase the rotational speed of the air leaving the stator and entering the interior of the rotor.

First claim

What we claim is:

1. A turbine engine comprising:
an engine core having a compressor section, a combustor section, and a turbine section in axial arrangement and defining an engine centerline, and which are operationally separated into a stator fixed about the centerline and a rotor rotatable about the centerline;
a first swirler provided on the stator for inducing rotation of an airflow passing through the engine core; and
a second swirler provided on the rotor downstream of and in fluid communication with the first swirler for reducing a rotational speed of the airflow from the first swirler;
wherein the second swirler includes a plurality of circumferentially spaced blades, with at least some of the circumferentially spaced blades are angled between 30 and 60 degrees relative to the engine centerline.

2. The turbine engine of claim 1 further comprising a shaft having a plurality of apertures with the shaft disposed between the first swirler and the second swirler.

3. The turbine engine of claim 1 wherein the blades are linear.

4. The turbine engine of claim 1 wherein the blades have an airfoil shape.

5. The turbine engine of claim 1 wherein the first swirler includes a plurality of circumferentially spaced vanes to induce circumferential rotation of the airflow.

6. The turbine engine of claim 1 wherein the first swirler induces rotation of the airflow to between 80-300% of the rotational speed of the rotor.

7. The turbine engine of claim 6 wherein the second swirler is a deswirler to reduce the rotational speed of the airflow from the first swirler.

8. The turbine engine of claim 1 wherein the second swirler is a deswirler.

9. The turbine engine of claim 1 wherein the second swirler reduces the rotational speed of the airflow below a predetermined threshold tangential Mach number.

10. The turbine engine of claim 9 wherein the predetermined threshold tangential Mach number is 0.4.

11. A turbine engine comprising a compressor section and a turbine section in axial arrangement and defining a stator and a rotor arranged about an engine centerline, with a first swirler provided with the stator for inducing a rotation on an airflow, and a second swirler provided with the rotor downstream of the first swirler for changing a rotational speed of the airflow provided from the first swirler, wherein the second swirler includes a plurality of circumferentially spaced blades angled to increase the rotational speed of the airflow provided from the first swirler.

12. The turbine engine of claim 11 wherein at least some of the blades are angled at 75 degrees relative to the engine centerline.

13. The turbine engine of claim 11 wherein the first swirler induces rotation of the airflow to between 80-300% of the rotational speed of the rotor.

14. A method of swirling a fluid within a turbine engine, the method comprising:
swirling the fluid from a static portion of the turbine engine into a rotor portion of the turbine engine at a speed greater than the rotor portion to define a first swirled flow; and
swirling the first swirled flow within an interior of the rotor portion and to maintain a predetermined Tangential Mach Number of 0.4 at a high pressure turbine.

15. The method of claim 14 wherein swirling the fluid further includes reducing a rotational speed of the fluid to match the rotational speed of the rotor portion at a first stage of the high pressure turbine.

16. The method of claim 14 wherein swirling the fluid further includes reducing a rotational speed of the fluid below a threshold tangential Mach number.

Assignees

• Gen Electric

Inventors

• Ziecina Pawel
• Mukherjee Shiladitya
• Weronko Jaroslaw
• Wachulec Marcin Krzysztof
• Jarboe Daniel Tyler
• Truszczynski Michal
• Michalec Piotr
• Trzepiota Pawel
• Fortuna Douglas Marti

Classifications

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• F05D2240/127

  Vortex generators, turbulators, or the like, for mixing · CPC title

• F05D2260/96

  Preventing, counteracting or reducing vibration or noise · CPC title

• F05D2260/14

  Preswirling · CPC title

• F05D2240/12

  Fluid guiding means, e.g. vanes · CPC title