High pitch-to-chord turbine airfoils

Patent metadata

Field	Value
Publication number	US-10294795-B2
Application number	US-76882210-A
Country	US
Kind code	B2
Filing date	Apr 28, 2010
Priority date	Apr 28, 2010
Publication date	May 21, 2019
Grant date	May 21, 2019

Abstract

A low pressure turbine engine component for use in an engine, for propelling a vehicle such as an aircraft is formed by a disk portion and a plurality of low pressure turbine blades extending outwardly from the disk portion. Each of the low pressure turbine blades has an airfoil portion with an axial chord length and a trailing edge. The low pressure turbine blades are spaced apart so that there is a pitch-to-chord ratio greater than 1.4, wherein the pitch is a distance between the trailing edges of adjacent ones of the low pressure turbine blades and the chord is the axial chord length of the blades.

First claim

What is claimed is:

1. A geared gas turbine engine for propelling a vehicle, said engine comprising:
a single geared gas turbine engine propulsive fan and at least one geared gas turbine engine low pressure turbine stage;
said fan and said at least one low pressure turbine stage being connected by a shaft;
a geared gas turbine engine gearbox incorporated into said shaft, said gearbox configured to rotationally decouple said at least one low pressure turbine stage and said shaft from said single geared gas turbine engine propulsive fan, wherein said at least one geared gas turbine low pressure turbine stage and said shaft decouple to rotate at higher speed than said single geared gas turbine engine propulsive fan; and
said at least one low pressure turbine stage being formed by a disk portion, a plurality of low pressure turbine blades extending outwardly from said disk portion, each of said low pressure turbine blades having an airfoil portion with an axial chord length and a trailing edge, and said turbine blades being spaced apart so that there is a pitch-to-chord ratio greater than 1.4, wherein said pitch is a distance between the trailing edges of adjacent ones of said turbine blades and said chord is the axial chord length of said blades, and wherein said pitch-to-chord ratio is measured at a mid-span of said blades, and said low pressure turbine blades including a high velocity ratio, said high velocity ratio being the ratio of the velocity of air exiting a turbine blade outlet proximate the trailing edge compared to the velocity of the air entering a low pressure turbine blade inlet opposite said outlet of said blades.

2. A geared gas turbine engine according to claim 1 , wherein said plurality of blades is arranged in a row.

3. A geared gas turbine engine according to claim 1 , wherein said plurality of blades are arranged in a plurality of rows and said blades in each said row have said pitch-to-chord ratio greater than 1.4.

4. A geared gas turbine engine according to claim 1 , wherein each said blade is formed from a nickel based superalloy material.

5. A geared gas turbine engine according to claim 1 , wherein each of said low pressure turbine blades is unshrouded.

6. A geared gas turbine engine low pressure turbine engine component for use in a geared gas turbine aircraft engine comprising:
a disk portion;
a plurality of geared gas turbine engine low pressure turbine blades extending outwardly from said disk portion, each of said geared gas turbine engine low pressure turbine blades having an airfoil portion with an axial chord length and a trailing edge;
said geared gas turbine engine low pressure turbine blades being configured to create a flow of air having a high velocity ratio, said flow of air entering an inlet and exiting an outlet opposite said inlet, said outlet proximate said trailing edge, said high velocity ratio being the ratio of the velocity of the air exiting the outlet compared to the velocity of the air entering the inlet;
said geared gas turbine engine low pressure turbine blades being spaced apart so that there is a pitch-to-chord ratio greater than 1.4, wherein said pitch is a distance between the trailing edges of adjacent ones of said geared gas turbine engine low pressure turbine blades and said chord is the axial chord length of said geared gas turbine engine low pressure turbine blades and wherein the pitch-to-chord ratio is measured at the mid-span of said geared gas turbine engine low pressure turbine blades.

7. The geared gas turbine engine low pressure turbine component of claim 6 , wherein said plurality of geared gas turbine engine low pressure turbine blades are arranged in a row.

8. The geared gas turbine engine low pressure turbine component of claim 6 , wherein said plurality of geared gas turbine engine low pressure turbine blades are arranged in a plurality of rows and said blades in each row have said pitch-to-chord ratio greater than 1.4.

9. The geared gas turbine engine low pressure turbine component of claim 6 , wherein each said blade is formed from a nickel based superalloy material.

Assignees

• Praisner Thomas J
• Estes Matthew B
• Jurek Renee J
• Huebner Norbert
• United Technologies Corp
• MTU Aero Engines AG

Inventors

• Praisner Thomas J
• Estes Matthew B
• Jurek Renee J
• Huebner Norbert

Classifications

• Y02T50/673

  Cross-Sectional Technologies · mapped topic

• F01D5/141 Primary

  Shape, i.e. outer, aerodynamic form (F01D5/148 - F01D5/20 take precedence; blade construction F01D5/147) · CPC title

• F05D2220/3215

  the last stage of the turbine · CPC title

• Y02T50/60

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