Turbomachine and turbine blade transfer
US-9957804-B2 · May 1, 2018 · US
Throat distribution for a rotor and rotor blade having camber and location of local maximum thickness distribution
US10859094B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-10859094-B2 |
| Application number | US-201816198279-A |
| Country | US |
| Kind code | B2 |
| Filing date | Nov 21, 2018 |
| Priority date | Nov 21, 2018 |
| Publication date | Dec 8, 2020 |
| Grant date | Dec 8, 2020 |
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- Title
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Abstract
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A rotor for a compressor includes a hub and a plurality of airfoils having a root, a tip opposite the root and a span that extends from 0% at the root to 100% at the tip. Each of the airfoils is coupled to the hub at the root and is spaced apart from adjacent ones of the airfoils over the span by a throat dimension. The throat dimension has a maximum value at a spanwise location between 60% of the span and 90% of the span of the adjacent ones of the airfoils, and at 10% of the span of the adjacent ones of the airfoils above or below the spanwise location of the maximum value, the throat dimension is less than 97% of the maximum value. The throat dimension at 5% of the span of the adjacent ones of the airfoils is less than 70% of the maximum value.
First claim
Opening claim text (preview).
What is claimed is: 1. A rotor for a compressor, comprising: a hub; and a plurality of airfoils having a root, a tip opposite the root and a span that extends from 0% at the root to 100% at the tip, each of the plurality of airfoils coupled to the hub at the root and spaced apart from adjacent ones of the plurality of airfoils over the span by a throat dimension defined between the adjacent ones of the plurality of airfoils, the throat dimension has a maximum value at a spanwise location between 60% of the span and 90% of the span of the adjacent ones of the plurality of airfoils, at 10% of the span of the adjacent ones of the plurality of airfoils above or below the spanwise location of the maximum value, the throat dimension is less than 97% of the maximum value, and the throat dimension between 90% of the span and the tip of the adjacent ones of the plurality of airfoils has a first value that is less than 70% of the maximum value. 2. The rotor of claim 1 , wherein the throat dimension between the root and 20% of the span of the adjacent ones of the plurality of airfoils has a second value that is less than 60% of the maximum value. 3. The rotor of claim 2 , wherein the throat dimension between the root and 20% of the span of the adjacent ones of the plurality of airfoils has a second value, and the second value is less than the first value. 4. The rotor of claim 3 , wherein the second value is between the root and 5% of the span of the adjacent ones of the plurality of airfoils. 5. The rotor of claim 1 , wherein the maximum value is between about 70% and 80% of the span of the adjacent ones of the plurality of airfoils. 6. The rotor of claim 1 , wherein the throat dimension decreases from the maximum value to the tip. 7. The rotor of claim 1 , wherein the rotor is a fan axial rotor associated with a gas turbine engine. 8. The rotor of claim 1 , wherein the throat dimension at 5% of the span of the adjacent ones of the plurality of airfoils is less than 70% of the maximum value. 9. A rotor for a compressor, comprising: a hub; and a plurality of airfoils having a root, a tip opposite the root and a span that extends from 0% at the root to 100% at the tip, each of the plurality of airfoils coupled to the hub at the root and spaced apart from adjacent ones of the plurality of airfoils over the span by a throat dimension defined between the adjacent ones of the plurality of airfoils, the throat dimension has a maximum value at a spanwise location between 60% of the span and 90% of the span of the adjacent ones of the plurality of airfoils, at 10% of the span of the adjacent ones of the plurality of airfoils above or below the spanwise location of the maximum value, the throat dimension is less than 97% of the maximum value, the throat dimension between 90% of the span and the tip of the adjacent ones of the plurality of airfoils has a first value, and the throat dimension between the root and 10% of the span of the adjacent ones of the plurality of airfoils has a second value that is less than 60% of the maximum value. 10. The rotor of claim 9 , wherein the second value is less than the first value. 11. The rotor of claim 9 , wherein the first value is less than 70% of the maximum value. 12. The rotor of claim 9 , wherein the second value is between the root and 5% of the span of the adjacent ones of the plurality of airfoils. 13. The rotor of claim 9 , wherein the maximum value is between about 70% and 80% of the span of the adjacent ones of the plurality of airfoils. 14. The rotor of claim 9 , wherein the first value is greater than 60% of the maximum value. 15. A rotor for a compressor, comprising: a hub; and a plurality of airfoils having a root, a tip opposite the root and a span that extends from 0% at the root to 100% at the tip, each of the plurality of airfoils coupled to the hub at the root and spaced apart from adjacent ones of the plurality of airfoils over the span by a throat dimension defined between the adjacent ones of the plurality of airfoils, the throat dimension has a maximum value at a spanwise location between 60% of the span and 90% of the span of the adjacent ones of the plurality of airfoils, at 10% of the span of the adjacent ones of the plurality of airfoils above or below the spanwise location of the maximum value, the throat dimension is less than 97% of the maximum value, the throat dimension between 90% of the span and the tip of the adjacent ones of the plurality of airfoils has a first value, the throat dimension between the root and 10% of the span of the adjacent ones of the plurality of airfoils has a second value that is less than 70% of the maximum value, the second value is less than the first value and the first value is less than 70% of the maximum value. 16. The rotor of claim 15 , wherein the second value is between the root and 5% of the span of the adjacent ones of the plurality of airfoils. 17. The rotor of claim 15 , wherein the maximum value is between about 70% and 80% of the span of the adjacent ones of the plurality of airfoils. 18. The rotor of claim 15 , wherein the first value is greater than 60% of the maximum value. 19. The rotor of claim 15 , wherein the throat dimension has a third value at the root, which is less than the second value.
Assignees
Inventors
Classifications
- F04D29/324Primary
Blades · CPC title
- F04D29/384Primary
characterised by form · CPC title
Shape, i.e. outer, aerodynamic form (F01D5/148 - F01D5/20 take precedence; blade construction F01D5/147) · CPC title
Cross-sectional characteristics · CPC title
related to the trailing edge of a rotor blade · CPC title
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Frequently asked questions
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- What does patent US10859094B2 cover?
- A rotor for a compressor includes a hub and a plurality of airfoils having a root, a tip opposite the root and a span that extends from 0% at the root to 100% at the tip. Each of the airfoils is coupled to the hub at the root and is spaced apart from adjacent ones of the airfoils over the span by a throat dimension. The throat dimension has a maximum value at a spanwise location between 60% of …
- Who is the assignee on this patent?
- Honeywell Int Inc
- What technology area does this patent fall under?
- Primary CPC classification F04D29/324. Mapped technology areas include Mechanical Engineering.
- When was this patent published?
- Publication date Tue Dec 08 2020 00:00:00 GMT+0000 (Coordinated Universal Time) (B2). Legal status and post-grant events are not shown on this page.
- What related patents are in patentsdb?
- We list 6 related publications on this page (citations in our corpus or others sharing the same primary CPC).